System and method for managing residual energy for an electric aircraft

ABSTRACT

A system for managing residual energy for an electric aircraft, wherein the system includes a battery pack incorporated in the electric aircraft, wherein the battery pack includes a plurality of battery modules and at least a pack monitor unit configured to generate a battery pack datum. The system further includes a charging component connected to the battery pack and a sensor connected to the charging component and configured to detect at least an electrical parameter of the charging component and the electric aircraft and generate a residual datum as a function of the at least an electrical parameter and the battery pack datum. The system further includes a computing device configured to receive the residual datum from the sensor, identify a residual element, generate an alert datum as a function of the residual element, and execute a security measure as a function of the alert datum.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of Nonprovisional application Ser.No. 17/515,458 filed on Oct. 30, 2021 and entitled “SYSTEM AND METHODFOR MANAGING RESIDUAL ENERGY FOR AN ELECTRIC AIRCRAFT,” the entirety ofwhich is incorporated herein by reference.

FIELD OF THE INVENTION

The present invention generally relates to the field of residual currentdetection. In particular, the present invention is directed to a systemand method for managing residual energy for an electric aircraft.

BACKGROUND

With the rise of electric vehicles, sufficient charging infrastructuresand systems are required to maintain proper and continuous operation ofelectrical vehicles for a variety of commercial applications. In theprocess of charging an electric battery of an electric vehicle, it iscritical to maintain the integrity of not only the electric vehicle, butalso the electric charger. The monitoring and management of such aprocess involving large scale electrical vehicular devices requireproper security protocols in the event of electrical hazards orpotential electrical hazards compared to preventative devices existingfor smaller electrical systems.

SUMMARY OF THE DISCLOSURE

In an aspect, a system for managing residual energy for an electricaircraft port is provided. The system includes: an electric aircraftport of an electric aircraft configured to facilitate communicationbetween a charging component and the electric aircraft via a chargingconnection; a battery pack connected to the electric aircraft port,wherein the battery pack includes: a plurality of battery modules; and apack monitor unit configured to generate a battery pack datum, whereinan electrical energy is transferred between the battery pack andcharging component via the charging connection; a sensor connected tothe electric aircraft port, wherein the sensor is configured to: detectan electrical parameter of the charging component when the chargingcomponent is in communication with the electric aircraft; and generate aresidual datum as a function of the electrical parameter and the batterypack datum; a computing device, wherein the computing device isconfigured to: receive the residual datum from the sensor; identify aresidual element as a function of the residual datum; generate an alertdatum as a function of the residual element; and execute a securitymeasure as a function of the alert datum.

In another aspect, a method for managing residual energy for an electricaircraft port is provided. The method includes: generating, by at leasta pack monitor unit of a battery pack, a battery pack datum from thebattery pack of an electric aircraft; creating a charging connectionbetween an electric aircraft port of the electric aircraft and acharging component; detecting, by a sensor connected to the electricaircraft port, an electrical parameter of the charging component;generating, by the sensor, a residual datum as a function of theelectrical parameter and the battery pack datum; receiving, by acomputing device, the residual datum; identifying a residual element asa function of the residual datum; generating an alert datum as afunction of the residual element; and executing a security measure as afunction of the alert datum.

These and other aspects and features of non-limiting embodiments of thepresent invention will become apparent to those skilled in the art uponreview of the following description of specific non-limiting embodimentsof the invention in conjunction with the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

For the purpose of illustrating the invention, the drawings show aspectsof one or more embodiments of the invention. However, it should beunderstood that the present invention is not limited to the precisearrangements and instrumentalities shown in the drawings, wherein:

FIG. 1 is a block diagram of an exemplary embodiment of a system formanaging residual energy for an electric aircraft;

FIG. 2 is a block diagram of an exemplary embodiment of a module monitorunit in one or more aspect of the present disclosure;

FIG. 3 is a block diagram of an exemplary embodiment of a battery packin one or more aspects of the present disclosure;

FIG. 4 is a block diagram of an exemplary embodiment of a batterymanagement system

FIG. 5 is a diagrammatic representation of an exemplary embodiments offuzzy sets for a residual threshold;

FIG. 6 is a flow diagram of an exemplary method for managing residualenergy for an electric aircraft;

FIG. 7 is an illustration of an exemplary embodiment of an electricaircraft;

FIG. 8 is an illustration of an exemplary embodiment of a sensor suitein partial cut-off view;

FIG. 9 is a block diagram of an exemplary machine-learning process; and

FIG. 10 is a block diagram of a computing system that can be used toimplement any one or more of the methodologies disclosed herein and anyone or more portions thereof.

The drawings are not necessarily to scale and may be illustrated byphantom lines, diagrammatic representations and fragmentary views. Incertain instances, details that are not necessary for an understandingof the embodiments or that render other details difficult to perceivemay have been omitted.

DETAILED DESCRIPTION

In the following description, for the purposes of explanation, numerousspecific details are set forth in order to provide a thoroughunderstanding of the present invention. It will be apparent, however,that the present invention may be practiced without these specificdetails. As used herein, the word “exemplary” or “illustrative” means“serving as an example, instance, or illustration.” Any implementationdescribed herein as “exemplary” or “illustrative” is not necessarily tobe construed as preferred or advantageous over other implementations.All of the implementations described below are exemplary implementationsprovided to enable persons skilled in the art to make or use theembodiments of the disclosure and are not intended to limit the scope ofthe disclosure, which is defined by the claims. For purposes ofdescription herein, the terms “upper”, “lower”, “left”, “rear”, “right”,“front”, “vertical”, “horizontal”, and derivatives thereof shall relateto orientations as illustrated for exemplary purposes in FIG. 4 .Furthermore, there is no intention to be bound by any expressed orimplied theory presented in the preceding technical field, background,brief summary or the following detailed description. It is also to beunderstood that the specific devices and processes illustrated in theattached drawings, and described in the following specification, aresimply embodiments of the inventive concepts defined in the appendedclaims. Hence, specific dimensions and other physical characteristicsrelating to the embodiments disclosed herein are not to be considered aslimiting, unless the claims expressly state otherwise.

In the following description, for the purposes of explanation, numerousspecific details are set forth in order to provide a thoroughunderstanding of the present invention. It will be apparent, however,that the present invention may be practiced without these specificdetails. As used herein, the word “exemplary” or “illustrative” means“serving as an example, instance, or illustration.” Any implementationdescribed herein as “exemplary” or “illustrative” is not necessarily tobe construed as preferred or advantageous over other implementations.All of the implementations described below are exemplary implementationsprovided to enable persons skilled in the art to make or use theembodiments of the disclosure and are not intended to limit the scope ofthe disclosure, which is defined by the claims.

At a high level, aspects of the present disclosure are directed tosystems and methods for managing residual energy for an electricaircraft. In an embodiment, aspects of the present disclosure can beused for any electric vehicles such as an electric aircraft, wherein theelectric aircraft is an electric vertical take-off and landing vehicle.In an embodiment, aspects of the present disclosure can be used todetect any electrical abnormality such as a leakage current. This is so,at least in part, to assign various types of residual faults to acurated response, wherein the response is designed to alert any user orcomputing system and perform preventative measures to resolve theelectrical abnormality or mitigate the damages caused by it.

Aspects of the present disclosure can be used to continuously monitorthe process of an electrical charge and check if any spikes inelectrical current, voltage, or any electrical outlier, calls for asecurity protocol. This is so, at least in part, to make sure that aninstance of a sign indicating a residual current is serious enough toexecute a security protocol. In an embodiment, a sensor may detect aleakage current, but the leakage current may return within a permissiblesafe limit, in which no drastic security protocol is required. This isso, at least in part, to prevent unnecessary and resource consumingmeasures in maximizing the safety and integrity of the system of thepresent disclosure.

Aspects of the present disclosure allow for human operators tophysically perform the security measures in the instance a leakagecurrent poses a serious danger. In another embodiment, aspects of thepresent disclosure can allow for automated or computing systems toexecute electrical protocols and programs to fulfill a security protocolto prevent the threats caused by a leakage current. In an embodiment,aspects of the present disclosure can include, at least in part, aresidual current device or a residual current circuit breaker. Exemplaryembodiments illustrating aspects of the present disclosure are describedbelow in the context of several specific examples.

Referring now to FIG. 1 , an exemplary embodiment of a system 100 for ashutdown of an electric charger in response to a fault detection isillustrated. In a non-limiting embodiment, system 100 may beincorporated with a recharging station which includes a recharginglanding pad and various infrastructure and/or equipment to support thefunctions of the components of system 100. A “recharging station,” forthe purpose of this disclosure, is an infrastructure that incorporates aplurality of equipment used to support the maintenance and charging ofany electric vehicles. In a non-limiting embodiment, system 100 may beused for electric aircraft 152. For instance and without limitation, therecharging station may be consistent with the recharging station in U.S.patent application Ser. No. 17/373,863 and titled, “SYSTEM FOR CHARGINGFROM AN ELECTRIC VEHICLE CHARGER TO AN ELECTRIC GRID,” which isincorporated in its entirety herein. In a non-limiting embodiment, therecharging station may include any infrastructure that may support thelanding, docking, charging, and the like thereof, of electric aircraft152 or a plurality of electric aircrafts. The recharging station mayinclude a docking terminal. A “docking terminal,” for the purposes ofthis disclosure, refers to an infrastructure or hub used to hold anelectric aircraft and/or connect electric devices. The docking terminalmay include charging component 132 that may be connected to electricaircraft port 156 of electric aircraft 152. Persons skilled in the art,upon reviewing the entirety of this disclosure, will be aware of variousembodiments of the recharging station that may house or support the useof charging component 132 for purposes as described.

With continued reference to FIG. 1 , in a non-limiting embodiment,system 100 may incorporate a recharging landing pad. A “recharginglanding pad,” for the purpose of this disclosure, is an infrastructuredesigned to support the landing and charging of a plurality of electricaircrafts. For instance and without limitation, the recharging landingpad may be consistent with the recharging landing pad in U.S. patentapplication Ser. No. 17/361,911 and title, “RECHARGING STATION FORELECTRIC AIRCRAFTS AND A METHOD OF ITS USE,” which is incorporated inits entirety herein. Recharging landing pad may incorporate system 100to charge electric aircrafts. In a non-limiting embodiment, sensor 104may be disposed on recharging landing pad. For example and withoutlimitation, sensor 104 may detect nearby electric aircrafts in the airwhich may be descending onto the electric aircraft. In a non-limitingembodiment, sensor 104 may be disposed on the recharging landing pad todetect, monitor, and maintain the descent, land, charging, and take-offof the electric aircraft onto the recharging pad. This is so, at leastin part, to accurately measure the electric aircraft wherein sensor 104is disposed on a location on the recharging landing pad that is ideal inconnecting incoming electric aircrafts to the recharging landing pad forrecharging. Persons skilled in the art, upon reviewing the entirety ofthis disclosure, will be aware of the various embodiments of therecharging landing pad and the configuration of the placement of sensor104 for purposes as described herein.

Still referring to FIG. 1 , system 100 includes computing device 112. Ina non-limiting embodiment, computing device 112 may include a flightcontroller. For instance and without limitation, the flight controllermay be consistent with the flight controller in U.S. patent applicationSer. No. 17/348,916 and titled, “METHODS AND SYSTEMS FOR SIMULATEDOPERATION OF AN ELECTRIC VERTICAL TAKE-OFF AND LANDING (EVTOL)AIRCRAFT,” which is incorporated herein in its entirety. Computingdevice 112 may include any computing device as described in thisdisclosure, including without limitation a microcontroller,microprocessor, digital signal processor (DSP) and/or system on a chip(SoC) as described in this disclosure. Computing device may include, beincluded in, and/or communicate with a mobile device such as a mobiletelephone or smartphone. computing device 112 may include a singlecomputing device operating independently, or may include two or morecomputing device operating in concert, in parallel, sequentially or thelike; two or more computing devices may be included together in a singlecomputing device or in two or more computing devices. computing device112 may interface or communicate with one or more additional devices asdescribed below in further detail via a network interface device.Network interface device may be utilized for connecting computing device112 to one or more of a variety of networks, and one or more devices.Examples of a network interface device include, but are not limited to,a network interface card (e.g., a mobile network interface card, a LANcard), a modem, and any combination thereof. Examples of a networkinclude, but are not limited to, a wide area network (e.g., theInternet, an enterprise network), a local area network (e.g., a networkassociated with an office, a building, a campus or other relativelysmall geographic space), a telephone network, a data network associatedwith a telephone/voice provider (e.g., a mobile communications providerdata and/or voice network), a direct connection between two computingdevices, and any combinations thereof. A network may employ a wiredand/or a wireless mode of communication. In general, any networktopology may be used. Information (e.g., data, software etc.) may becommunicated to and/or from a computer and/or a computing device.computing device 112 may include but is not limited to, for example, acomputing device or cluster of computing devices in a first location anda second computing device or cluster of computing devices in a secondlocation. computing device 112 may include one or more computing devicesdedicated to data storage, security, distribution of traffic for loadbalancing, and the like. computing device 112 may distribute one or morecomputing tasks as described below across a plurality of computingdevices of computing device, which may operate in parallel, in series,redundantly, or in any other manner used for distribution of tasks ormemory between computing devices. computing device 112 may beimplemented using a “shared nothing” architecture in which data iscached at the worker, in an embodiment, this may enable scalability ofsystem 100 and/or computing device.

With continued reference to FIG. 1 , computing device 112 may bedesigned and/or configured to perform any method, method step, orsequence of method steps in any embodiment described in this disclosure,in any order and with any degree of repetition. For instance, computingdevice 112 may be configured to perform a single step or sequencerepeatedly until a desired or commanded outcome is achieved; repetitionof a step or a sequence of steps may be performed iteratively and/orrecursively using outputs of previous repetitions as inputs tosubsequent repetitions, aggregating inputs and/or outputs of repetitionsto produce an aggregate result, reduction or decrement of one or morevariables such as global variables, and/or division of a largerprocessing task into a set of iteratively addressed smaller processingtasks. computing device 112 may perform any step or sequence of steps asdescribed in this disclosure in parallel, such as simultaneously and/orsubstantially simultaneously performing a step two or more times usingtwo or more parallel threads, processor cores, or the like; division oftasks between parallel threads and/or processes may be performedaccording to any protocol suitable for division of tasks betweeniterations. Persons skilled in the art, upon reviewing the entirety ofthis disclosure, will be aware of various ways in which steps, sequencesof steps, processing tasks, and/or data may be subdivided, shared, orotherwise dealt with using iteration, recursion, and/or parallelprocessing.

With continued reference to FIG. 1 , system 100 may include an electricvehicle. The electric vehicle may include any electrical vehicle inwhich persons skilled in the art, upon reviewing the entirety of thisdisclosure, will be aware of the various embodiments of an electricvehicle for purposes described in the entirety of this disclosure. In anon-limiting embodiment, the electrical vehicle may include electricaircraft 152. In a non-limiting embodiment, electric aircraft 152 mayinclude an eVTOL aircraft, a drone, an unmanned aerial vehicle (UAV), asatellite, and the like thereof. Electric aircraft 152 may includebattery pack 160 and electric aircraft port 156. Battery pack 156 mayinclude a battery module or a plurality of battery modules configured topower to electric aircraft 152. In a non-limiting embodiment, batterypack 156 may be configured to be recharged by a recharging station asdescribed herein. An “electric aircraft port,” for the purpose of thisdisclosure, is an interface configured to mate with any connector fortransferring electrical energy. In a non-limiting embodiment, electricaircraft port 156 may be connected to battery pack 160 wherein electricaircraft port 156 is configured to act as a medium for the transfer ofelectrical energy between battery pack 156 and any connector asdescribed in the entirety of this disclosure.

With continued reference to FIG. 1 , sensor 104 may include one or moresensors. As used in this disclosure, a “sensor” is a device that isconfigured to detect an input and/or a phenomenon and transmitinformation related to the detection. In a non-limiting embodiment,sensor 104 may be communicatively connected to charging component 132.“Communicatively connected”, for the purposes of this disclosure, is twoor more components electrically, or otherwise connected and configuredto transmit and receive signals from one another. For example, andwithout limitation, a sensor may transduce a detected chargingphenomenon and/or characteristic, such as, and without limitation,temperature, voltage, current, pressure, and the like, into a sensedsignal. In one or more embodiments, and without limitation, sensor 104may include a plurality of sensors. In one or more embodiments, andwithout limitation, sensor 104 may include one or more temperaturesensors, voltmeters, current sensors, hydrometers, infrared sensors,photoelectric sensors, ionization smoke sensors, motion sensors,pressure sensors, radiation sensors, level sensors, imaging devices,moisture sensors, gas and chemical sensors, flame sensors, electricalsensors, imaging sensors, force sensors, Hall sensors, and the like.Sensor 104 may be a contact or a non-contact sensor. For instance, andwithout limitation, sensor 104 may be connected to electric aircraft152, electric aircraft port 156, charging component 132, and/or acomputing device 112. In other embodiments, sensor 104 may be remote toelectric aircraft 152, electric aircraft port 156, charging component132, and/or computing device 112. In a non-limiting embodiment,computing device 112 may include a pilot control, a controller, such asa flight controller, and the like thereof. In one or more embodiments,sensor 104 may transmit/receive signals to/from computing device 112.Signals may include electrical, electromagnetic, visual, audio, radiowaves, or another undisclosed signal type alone or in combination.

With continued reference to FIG. 1 , sensor 104 may include a clampmeter. In a non-limiting embodiment, the clamp meter may detect andmeasure a wide range of alternating or changing currents passing througha conductor under test. For example and without limitation, whentelecommunications equipment is present, the value of leakage indicatedby a clamp meter may be considerably more than that resulting frominsulation impedance at 60 Hz. This is because telecommunicationsequipment typically incorporates filters that produce functionalgrounding currents and other equipment that produces harmonics, etc. Youcan only measure the characteristic leakage at 60 Hz by using a clampmeter that incorporates a narrow band-pass filter for removing currentsat other frequencies. In a non-limiting embodiment, sensor 104 mayinclude any meter specially designed for measuring leakage currents. Thecurrent flowing in the ground conductor is measured by connecting themeter in series with the grounding connection. In a non-limitingembodiment, for electrical devices incorporating a computing device, theground connection is opened and the current flowing to the neutral sideof the power line is measured. In another non-limiting embodiment, forelectrical devices used for medical purposes, the current flowing toground is measured. In a non-limiting embodiment, the meter may also beconnected between the outputs of the power supply such as batterystorage unit 176 and ground. In a non-limiting embodiment, chargingcomponent 132 may include a ground or connected to a ground. In anothernon-limiting embodiment, electric aircraft 152 may be connected to thesame ground for purposes as described herein. In an embodiment, themeter may measure alternating currents by conducting a test, wherein thetest conditions include swapping the ac line and neutral connections,and turning power switches off and on while monitoring the current. Thetest is performed after the equipment has warmed to normal operatingtemperature and, in some cases, following certain test that causeabnormally high temperatures within the equipment. This is so, at leastin part, to identify and measure the worst-case leakage current. Forvery low leakage currents, the meter is replaced with a networkconsisting of either a resistor or a resistor and capacitor combination.The voltage drop across the network is then measured using a sensitiveac voltmeter. Ungrounded or double-insulated equipment is checked byconnecting the meter between any touchable conductive part and ground.In the case of non-conductive housings, a copper foil of a specific sizeis placed on the housing, and the current flowing from it to ground ismeasured. Persons skilled in the art, upon reviewing the entirety ofthis disclosure, will be aware of the various embodiments of using aclamp meter for detecting and measuring residual element 116.

With continued reference to FIG. 1 , sensor 104 may include a pluralityof independent sensors, where any number of the described sensors may beused to detect any number of physical or electrical quantitiesassociated with communication of the charging connection. Independentsensors may include separate sensors measuring physical or electricalquantities that may be powered by and/or in communication with circuitsindependently, where each may signal sensor output to a computing device112 such as a user graphical interface. In an embodiment, use of aplurality of independent sensors may result in redundancy configured toemploy more than one sensor that measures the same phenomenon, thosesensors being of the same type, a combination of, or another type ofsensor not disclosed, so that in the event one sensor fails, the abilityof sensor 104 to detect phenomenon may be maintained.

With continued reference to FIG. 1 , sensor 104 may further include asensor suite. Signals may include electrical, electromagnetic, visual,audio, radio waves, or another undisclosed signal type alone or incombination. Any datum or signal herein may include an electricalsignal. Electrical signals may include analog signals, digital signals,periodic or aperiodic signal, step signals, unit impulse signal, unitramp signal, unit parabolic signal, signum function, exponential signal,rectangular signal, triangular signal, sinusoidal signal, sinc function,or pulse width modulated signal. At least a sensor 104 may includecircuitry, computing devices, electronic components or a combinationthereof that translates residual datum 108 into at least an electronicsignal configured to be transmitted to another electronic component.

With continued reference to FIG. 1 , in one or more embodiments, sensor104 may include electrical sensors. Electrical sensors may be configuredto measure voltage across a component, electrical current through acomponent, and resistance of a component. In one or more embodiments,sensor 104 may include thermocouples, thermistors, thermometers,infrared sensors, resistance temperature sensors (RTDs), semiconductorbased integrated circuits (ICs), a combination thereof, or anotherundisclosed sensor type, alone or in combination. Temperature, for thepurposes of this disclosure, and as would be appreciated by someone ofordinary skill in the art, is a measure of the heat energy of a system.Temperature, as measured by any number or combinations of sensorspresent within sensor 104, may be measured in Fahrenheit (° F.), Celsius(° C.), Kelvin (° K), or another scale alone or in combination. Thetemperature measured by sensors may comprise electrical signals, whichare transmitted to their appropriate destination wireless or through awired connection. In some embodiments, sensor 104 may include aplurality of sensing devices, such as, but not limited to, temperaturesensors, humidity sensors, accelerometers, electrochemical sensors,gyroscopes, magnetometers, inertial measurement unit (IMU), pressuresensor, proximity sensor, displacement sensor, force sensor, vibrationsensor, air detectors, hydrogen gas detectors, and the like.

Exemplary methods of signal processing may include analog, continuoustime, discrete, digital, nonlinear, and statistical. Analog signalprocessing may be performed on non-digitized or analog signals.Exemplary analog processes may include passive filters, active filters,additive mixers, integrators, delay lines, compandors, multipliers,voltage-controlled filters, voltage-controlled oscillators, andphase-locked loops. Continuous-time signal processing may be used, insome cases, to process signals which varying continuously within adomain, for instance time. Exemplary non-limiting continuous timeprocesses may include time domain processing, frequency domainprocessing (Fourier transform), and complex frequency domain processing.Discrete time signal processing may be used when a signal is samplednon-continuously or at discrete time intervals (i.e., quantized intime). Analog discrete-time signal processing may process a signal usingthe following exemplary circuits sample and hold circuits, analogtime-division multiplexers, analog delay lines and analog feedback shiftregisters. Digital signal processing may be used to process digitizeddiscrete-time sampled signals. Commonly, digital signal processing maybe performed by a computing device or other specialized digitalcircuits, such as without limitation an application specific integratedcircuit (ASIC), a field-programmable gate array (FPGA), or a specializeddigital signal processor (DSP). Digital signal processing may be used toperform any combination of typical arithmetical operations, includingfixed-point and floating-point, real-valued and complex-valued,multiplication and addition. Digital signal processing may additionallyoperate circular buffers and lookup tables. Further non-limitingexamples of algorithms that may be performed according to digital signalprocessing techniques include fast Fourier transform (FFT), finiteimpulse response (FIR) filter, infinite impulse response (IIR) filter,and adaptive filters such as the Wiener and Kalman filters. Statisticalsignal processing may be used to process a signal as a random function(i.e., a stochastic process), utilizing statistical properties. Forinstance, in some embodiments, a signal may be modeled with aprobability distribution indicating noise, which then may be used toreduce noise in a processed signal.

With continued reference to FIG. 1 , in one or more embodiments, sensor104 may include a sensor suite which may include a plurality of sensorsthat may detect similar or unique phenomena. For example, in anon-limiting embodiment, a sensor suite may include a plurality ofvoltmeters or a mixture of voltmeters and thermocouples. System 100 mayinclude a plurality of sensors in the form of individual sensors or asensor suite working in tandem or individually. A sensor suite mayinclude a plurality of independent sensors, as described in thisdisclosure, where any number of the described sensors may be used todetect any number of physical or electrical quantities associated with acharging connection. Independent sensors may include separate sensorsmeasuring physical or electrical quantities that may be powered byand/or in communication with circuits independently, where each maysignal sensor output to a computing device 112 such as computing device112. In an embodiment, use of a plurality of independent sensors mayresult in redundancy configured to employ more than one sensor thatmeasures the same phenomenon, those sensors being of the same type, acombination of, or another type of sensor not disclosed, so that in theevent one sensor fails, the ability to detect phenomenon is maintained.In one or more embodiments, sensor 104 may include a sense board. Asense board may have at least a portion of a circuit board that includesone or more sensors configured to, for example, measure a temperature ofbattery pack 160 of electric aircraft 152, battery storage unit 176incorporated with charging component 132, and the like thereof. In oneor more embodiments, a sense board may be connected to one or morebattery modules or cells of a power source. In one or more embodiments,a sense board may include one or more circuits and/or circuit elements,including, for example, a printed circuit board component. A sense boardmay include, without limitation, computing device 112 configured toperform and/or direct any actions performed by the sense board and/orany other component and/or element described in this disclosure. Thecomputing device 112 may include any analog or digital control circuit,including without limitation a combinational and/or synchronous logiccircuit, a processor, microprocessor, microcontroller, or the like.

With continued reference to FIG. 1 , sensor 104 is configured to detectat least an electrical parameter of a charging component 132. An“electrical parameter,” for the purpose of this disclosure, is acollection of information describing any events related to anyelectrical process involved in the charging of an electric device. In anon-limiting embodiment, the plurality of measured charge may include acollection of information describing the electric vehicle that may becharged. For example and without limitation, the plurality of measuredcharge may include, but not limited to, electric current, electriccharge, electric voltage, battery temperature, electric aircraft, andthe like thereof. In a non-limiting embodiment, sensor 104 may beconfigured to capture any unusual data inputs such as, but not limitedto, electric shock, electric overcharge, electric charge, a shortconnection and the like thereof. In an embodiment, sensor 104 may beconfigured to look for data inputs that may cause any abnormal eventsrelated to charging. For example and without limitation, sensor 104 maybe configured to play closer attention to battery temperature, electriccharge cycle, and the like thereof, which may be a catalyst forpotential abnormal events. Persons skilled in the art, upon reviewingthe entirety of this disclosure, will be aware of the variousembodiments of charger related data for purposes described herein.

With continued reference to FIG. 1 , sensor 104 may be configured togenerate a residual datum 108 as a function of the at least anelectrical parameter. A “residual datum,” for the purpose of thisdisclosure, is any datum or element of data describing parameterscaptured by sensor 104 which may include a collection of informationdescribing the patterns and factors of electrical energy involved withcharging component 132, electric aircraft 152, or the process ofcharging. In a non-limiting embodiment, residual datum 108 may be astandardized collection of data of the at least an electrical parameter,wherein residual datum 108 may include a plurality of categoriesdenoting information about electric aircraft 152, battery pack 160,charging component 132, and the like thereof. For example and withoutlimitation, residual datum 108 may include, but is not limited to,battery quality, battery life cycle, remaining battery capacity,electric current, electric voltage, pressure, temperature, moisturelevel, and the like. In a non-limiting embodiment, residual datum 108may include any data captured by any sensor as described in the entiretyof this disclosure. Additionally and alternatively, residual datum 108may include any element or signal of data that represents an electricaircraft route and various environmental or outside parameters. In anon-limiting embodiment, residual datum 108 may include a degree oftorque that may be sensed, without limitation, using load sensorsdeployed at and/or around a propulsor and/or by measuring backelectromotive force (back EMF) generated by a motor driving thepropulsor. In an embodiment, use of a plurality of independent sensorsmay result in redundancy configured to employ more than one sensor thatmeasures the same phenomenon, those sensors being of the same type, acombination of, or another type of sensor not disclosed, so that in theevent one sensor fails, the ability to detect phenomenon is maintainedand in a non-limiting example, a user alter aircraft usage pursuant tosensor readings. One of ordinary skill in the art will appreciate, afterreviewing the entirety of this disclosure, that motion may include aplurality of types including but not limited to: spinning, rotating,oscillating, gyrating, jumping, sliding, reciprocating, or the like.

With continued reference to FIG. 1 , sensor 104 may receive a batterypack datum from electric aircraft 152. The battery pack datum may bepart of residual datum 108. A “battery pack datum,” for the purpose ofthis disclosure, is a collection of information describing one or morecharacteristics corresponding to at least a portion of a battery pack ofan electric aircraft and/or its components. Sensor 104 may be configuredto detect a at least an electrical parameter from battery pack 160 as apart of residual datum 108. In a non-limiting embodiment, the batterypack datum may include any data and/or information about the state ofthe battery pack. the battery pack datum may include information aboutthe make and model of the battery pack, rate of recharge of the batterypack, rate of discharge of the battery pack, and the like thereof. Thisis so, at least in part, to provide information that may be used tocharge the electric aircraft with a compatible electric charging deviceand optimal amount of electric energy. In a non-limiting embodiment, thebattery pack datum may be generated by a sensor communicativelyconnected to battery pack 160 and transmitted to sensor 104 and/orcomputing device 112. Persons skilled in the art, upon reviewing theentirety of this disclosure, will be aware of the various batteryinformation used for charging and purposes as described herein.

With continued reference to FIG. 1 , residual datum 108 may includeinformation indicative of the location of charging component 132relative to electric aircraft port 156. In a non-limiting embodiment,sensor 104 may detect the proximity of electric aircraft port 132relative to charging component 132 of the recharging landing pad ofsystem 100. For example and without limitation, sensor 104 disposed oncharging component 132 may detect if electric aircraft 152 and itselectric aircraft port 156 are within a certain distance for chargingcomponent 132 to physically form a connection with electric aircraftport 156 to transfer electric energy. In a non-limiting embodiment,sensor 104 may be disposed onto an infrastructure designed to supportthe landing and charging of a plurality of electric aircrafts.“Disposed,” for the purpose of this disclosure, is the physicalplacement of a computing device on an actuator. In another non-limitingexample, residual datum 108 may inform computing device 112 if electricaircraft 152 is too far for charging component 132 to reach electricaircraft port 156 of electric aircraft 152, wherein computing device 112may generate an alert to inform any personnel or electric aircraft 152of the situation. Persons skilled in the art, upon reviewing theentirety of this disclosure, will be aware of the various embodiments ofproximity data for accurate and safe charging and connection forpurposes as described herein.

With continued reference to FIG. 1 , residual datum 108 may include abattery parameter set. A “battery parameter set,” for the purpose ofthis disclosure, is an element of data representing physical valuesand/or identifiers of an electric aircraft, the electric aircraft'sactuators and/or flight components, and the electric aircraft's chargingcomponents. For instance and without limitation, the battery parameterset may be consistent with the battery parameter set in U.S. patentapplication Ser. No. 17/407,518 and titled, “SYSTEM AND METHOD FORCOMMUNICATING A PRE-CHARGING PACKAGE STREAM OF AN ELECTRIC AIRCRAFT,”which is incorporated in its entirety herein. For example and withoutlimitation, electric aircraft 152 may generate its own battery parameterset in which the pilot of electric aircraft 152 may transmit the batteryparameter set to computing device 112, which may be first receivedand/or detected by sensor 104, through any means of digitalcommunication, which may include being connected to a network, in orderfor computing device 112 to generate security measure 120 for electricaircraft 152. This is so, at least in part, to provide computing device112 useful information in generating security measure 120 tailored toelectric aircraft 152 or to any other electric aircraft.

With continued reference to FIG. 1 , the battery parameter set mayinclude a datum including battery parameters. Any datum or signal hereinmay include an electrical signal. Electrical signals may include analogsignals, digital signals, periodic or aperiodic signal, step signals,unit impulse signal, unit ramp signal, unit parabolic signal, signumfunction, exponential signal, rectangular signal, triangular signal,sinusoidal signal, sinc function, or pulse width modulated signal.Sensor may include circuitry, computing devices, electronic componentsor a combination thereof that translates any datum into at least anelectronic signal configured to be transmitted to another electroniccomponent. Any datum or signal herein may include an electrical signal.Electrical signals may include analog signals, digital signals, periodicor aperiodic signal, step signals, unit impulse signal, unit rampsignal, unit parabolic signal, signum function, exponential signal,rectangular signal, triangular signal, sinusoidal signal, sinc function,or pulse width modulated signal. The battery parameter set may include aplurality of individual battery parameters. A “battery parameter,” forthe purposes of this disclosure, refers to a measured value associatedwith electric aircraft 152 its battery pack. Battery parameter mayinclude a state of charge of the battery pack. A “state of charge,” forthe purposes of this disclosure, refers to the level of charge of theelectric battery relative to its capacity. Battery parameter may includea charge cycle. A “charge cycle,” for the purposes of this disclosure,refers the process of charging a rechargeable battery and discharging itas required into a load. The term is typically used to specify abattery's expected life, as the number of charge cycles affects lifemore than the mere passage of time. A person of ordinary skill in theart, after viewing the entirety of this disclosure, would appreciate theplurality of measured values in the context of battery charging.

With continued reference to FIG. 1 , the battery parameter set mayinclude at least a charge requirement. A “charge requirement, for thepurpose of this disclosure, refers to an element of data representingphysical or electronic values that identify compatible parameters forcharging. The at least charge requirement may include, but not limitedto, battery capacity of the electric aircraft, battery charge cycle,maximum battery capacity, minimum battery capacity, and the likethereof. The at least a charge requirement may include a plurality ofmaximum charge current for a plurality of battery types. In anon-limiting embodiment, charge requirement may include a minimum chargecurrent to be 15% to 25% of the maximum battery capacity of a batterypack of electric aircraft 152. In a non-limiting embodiment, the atleast a charge requirement may include a maximum charging current to be50% for a gel battery, 50% for an AGM battery and the like thereof. In anon-limiting embodiment, the at least a charge requirement may include aplurality of different types of chargers designated for different typesof electric aircrafts, different types of electric aircraft batteries,and different types of charging.

With continued reference to FIG. 1 , in a non-limiting embodiment, theat least charge requirement may include a classification label for typeof charger to be used on a battery pack in which the battery pack isassigned a classification label based on the quality of life of thebattery pack. For example and without limitation, electric aircraft 152with a low level classification level may denote a level 1 charger to beused which may be included in the battery parameter set. For instance, abattery pack with a degraded quality of life and/or smaller capacitiveload may be designated a level 1 charger configured to slowly charge thebattery pack to avoid exposure to high electric current that may lead toconsiderable stress or damage to the battery pack and electric aircraft152. For example and without limitation, the battery pack may bedesignated to a low level classification label as a function of thepriority of the charging of the electric aircraft. In a non-limitingembodiment, the battery parameter set may include information regardingthe type of travel of an electric aircraft. For example and withoutlimitation, if electric aircraft 152 is intended to fly a low priorityflight, the battery parameter set may denote a low level classificationlabel to the electric aircraft 152 in which a level 1 charger may beassigned to charge electric aircraft 152. For example and withoutlimitation, the at least a charge requirement of the battery parameterset for electric aircraft 152 may include a charge duration of 40 hours.In a non-limiting embodiment, a battery pack of electric aircraft 152may be classified with an average level classification label and denotethe use of a level 2 charger. For example and without limitation,electric aircraft 152 intended for a long flight may denote a level 2charger and average level classification label in which the batteryparameter set may denote such information and designate a level 2charger to better charge the electric aircraft 152 as a result of thebattery parameter set. For example and without limitation, the batteryparameter set denoting an average level classification label may includethe at least a charge requirement containing a charge rate of 6 kW. In anon-limiting embodiment, the battery parameter set for electric aircraftwith an average level classification label may include a charge durationof 6 hours. In a non-limiting embodiment, a high level classificationlabel may be assigned to an electric aircraft 152 and denote a level 5charger for high priority flights. In a non-limiting embodiment, a highlevel classification label may be assigned to electric aircraft 152 witha battery pack containing a high capacitive load which may endure fastelectrical current. For example and without limitation, electricaircraft 152 that may be intended to fly important persons or emergencyflights may denote a high level classification label in which thebattery parameter set may assign the electric aircraft to a level 5charger for fast charging of electric aircraft 152. For example andwithout limitation, High level classification label may include the atleast a charge requirement containing a charge rate of 50-60 kW. In anon-limiting embodiment, the battery parameter set for an electricaircraft with a high level classification label may include a chargeduration of 2 hours. A person of ordinary skill in the art, afterviewing the entirety of this disclosure, would appreciate the chargerequirement identifying an electric aircraft in the context ofbatteries.

With continued reference to FIG. 1 , the battery parameter set furtherincludes at least a charging parameter. A “charging parameter,” for thepurposes of this disclosure, refers to a measure value associate withthe charging of a power source of an electric aircraft. At least acharging parameter may include any data associated with charging of thebattery of an electric aircraft. For example and without limitation, atleast a charging parameter may include a target charge voltage for thebattery, battery capacity, maximum charging time, and the like. In anon-limiting embodiment, the charging parameter may denote a specifictype of charging and charger associated with the electric vehicle. Forexample and without limitation, electric aircraft 152 may be assigned toa trickle charging in which electric aircraft 152 is configured toreceive a trickle charge. In a non-limiting embodiment, chargingparameter may include a classification label as described in theentirety of this disclosure. In a non-limiting embodiment, chargingparameter may include a plurality of data describing battery parametersincluding, but not limited to, battery type, battery life cycle, and thelike thereof. For example and without limitation, battery parameter mayinclude a life cycle of 5 years. For example and without limitation,battery parameter may include battery types such as, but not limited to,lead acid, nickel cadmium (NiCd), nickel-metal hydride (Ni-MH),lithium-ion/lithium polymer, lithium metal, and the like thereof. In anon-limiting embodiment, battery parameter may include a plurality ofthreats associated with a battery pack. For example and withoutlimitation, the battery parameter set may include threats such as, butnot limited to, battery leakage, battery overcharging, excessive batterycharging rate, excessive battery discharge rate, battery bus fault, andthe like thereof.

Still referring to FIG. 1 , for instance, and without limitation, sensor104 may detect a connection status, which may be detected as part ofresidual datum 108. A “connection status,” for the purpose of thisdisclosure, is a determination of a presence of a connection is present,established, and/or disconnected between charging component 132 andelectric aircraft 152 and/or electric aircraft port 156. For example andwithout limitation, the connection status may include a booleanclassification denoting that a connection is made or not. In anothernon-limiting example, the connection status may include a status of“pending” wherein sensor 104 recognizes that a connection is to be madeand monitors the process of establishing a connection between chargingcomponent 132 and electric aircraft 152 and its electric aircraft port156. In a non-limiting embodiment, the connection status may include astatus of “connected,” denoting that a connection has been successfullyestablished. For example and without limitation, sensor 104 may monitorthe connecting process and transmit a confirmation signal to computingdevice 112 that the connection is valid and successfully made. Inanother non-limiting embodiment, the connection status may include astatus of “disconnected,” denoting that a connection has been properlyand/or successfully disconnected between charging component 132 andelectric aircraft 152 and its electric aircraft port 156. For exampleand without limitation, after the completion of a successful action bycharging component 132 and electric aircraft 152, the connection betweenthem may be disconnected to ensure the completion of a charging process.A “charging process,” for the purposes of this disclosure, is anyprocess of electrical energy transfer between two or more electricaldevices. In a non-limiting embodiment, the charging process may includecharging component 132 power electric aircraft 152 and its battery pack.For example and without limitation, charging component 132 may use itsown source and/or storage of electrical energy such as battery storageunit 176 to power the battery pack of electric aircraft 152.

Still referring to FIG. 1 , system 100 may include charging component132. In a non-limiting embodiment, sensor 104 may be disposed ontocharging component 132. In another non-limiting embodiment, chargingconnector may be electrically connected to computing device 112. A“charging component,” for the purpose of this disclosure, is anyphysical connector used as a hub of transfer for electrical energy whichmay include a distal end of a tether or a bundle of tethers, e.g., hose,tubing, cables, wires, and the like, which is configured to removablyattach with a mating component, for example without limitation a port.As used in this disclosure, a “port” is an interface for example of aninterface configured to receive another component or an interfaceconfigured to transmit and/or receive signal on a computing device. Forinstance and without limitation, charging component 132 may beconsistent with the charging connector in U.S. patent application Ser.No. 17/407,518 and titled, “SYSTEM AND METHOD FOR COMMUNICATING APRE-CHARGING PACKAGE STREAM OF AN ELECTRIC AIRCRAFT,” which isincorporated in its entirety herein. In a non-limiting embodiment,charging component 132 may connect to the electric aircraft 152 viaelectric aircraft port 156. An “electric aircraft port,” for the purposeof this disclosure, is an interface configured to mate with anyconnector for transferring electrical energy. For example and withoutlimitation, sensor 104 may be attached onto charging component 132 tobetter detect location relativity of charging component 132 to electricaircraft port 156. In a non-limiting embodiment, charging component 132may mate with electric aircraft port 156 as a function of sensor 104disposed onto charging component 132 and forming a physical connectionand/or mechanical connection. In a non-limiting embodiment, chargingcomponent 132 may include a male component having a penetrative form andport may include a female component having a receptive form, receptiveto the male component. Alternatively or additionally, charging component132 may have a female component and port may have a male component. Insome cases, connector may include multiple connections, which may makecontact and/or communicate with associated mating components withinport, when the connector is mated with the port. In a non-limitingembodiment, charging component 132 may include a housing. As used inthis disclosure, a “housing” is a physical component within which otherinternal components are located. In some cases, internal components withhousing will be functional while function of housing may largely be toprotect the internal components. The housing and/or connector may beconfigured to mate with a port, for example an electric aircraft port156. As used in this disclosure, “mate” is an action of attaching two ormore components together. Mating may be performed using a mechanical orelectromechanical means described in this disclosure. For example,without limitation mating may include an electromechanical device usedto join electrical conductors and create an electrical circuit. In somecases, mating may be performed by way of gendered mating components. Agendered mate may include a male component or plug which is insertedwithin a female component or socket. In some cases, mating may beremovable. In some cases, mating may be permanent. In some cases, matingmay be removable, but require a specialized tool or key for removal.Mating may be achieved by way of one or more of plug and socket mates,pogo pin contact, crown spring mates, and the like. In some cases,mating may be keyed to ensure proper alignment of charging component132. In some cases, mate may be lockable. As used in this disclosure, an“electric vehicle” is any electrically power means of human transport,for example without limitation an electric aircraft or electric verticaltake-off and landing aircraft. In some cases, an electric vehicle willinclude a battery pack configured to power at least a motor configuredto move the electric aircraft 104. In a non-limiting embodiment,electric aircraft port 156 may be configured to support bidirectionalcharging. A “bidirectional charging,” for the purpose of thisdisclosure, is a charging that allows for the flow of electricity to gotwo ways. In a non-limiting embodiment, charging component 132 mayprovide electric energy to the battery pack of an electric aircraft froma power source such as an electric grid and also receive electric energyfrom an electric aircraft and its battery pack. For example and withoutlimitation, electric aircraft port 156 may act as a hub for the transferof electrical energy. In a non-limiting embodiment, electric aircraftport 156 may be integrated into a system supporting vehicle-to-grid(V2G) charging. For example and without limitation, electric aircraftport may be used to transfer electric energy from the battery pack of anelectric aircraft 152 to charge a power source and/or battery pack of acharging component 132. Charging component 132 may include a universalcharger and/or common charger. For example and without limitation,charging component 132 may draw power from a variety of input voltages.Persons skilled in the art, upon reviewing the entirety of thisdisclosure, will be aware of various configurations of the electricaircraft port 156 that may be utilized for various chargingmethodologies consistent with this disclosure.

Still referring to FIG. 1 , charging component 132 may be configured tocharge and/or recharge a plurality of electric aircrafts at a time usingat least any charger as described in the entirety of this disclosure. Asused in this disclosure, “charging” is a process of flowing electricalcharge in order to increase stored energy within a power source. In oneor more non-limiting exemplary embodiments, a power source includes abattery and charging includes providing an electrical current to thebattery. In some embodiments, charging component 132 may be constructedfrom any of variety of suitable materials or any combination thereof. Insome embodiments, charger 104 may be constructed from metal, concrete,polymers, or other durable materials. In one or more embodiments,charging component 132 may be constructed from a lightweight metalalloy. The charging pad may include a landing pad, where the landing padmay be any designated area for the electric vehicle to land and/ortakeoff. In one or more embodiments, landing pad may be made of anysuitable material and may be any dimension. In some embodiments, landingpad may be a helideck or a helipad. In a non-limiting examples of activecurrent sources include active current sources without negativefeedback, such as current-stable nonlinear implementation circuits,following voltage implementation circuits, voltage compensationimplementation circuits, and current compensation implementationcircuits, and current sources with negative feedback, including simpletransistor current sources, such as constant currant diodes, Zener diodecurrent source circuits, LED current source circuits, transistorcurrent, and the like, Op-amp current source circuits, voltage regulatorcircuits, and curpistor tubes, to name a few. In some cases, one or morecircuits within charger 104 or within communication with charger 104 areconfigured to affect electrical recharging current according to controlsignal from, for example, a controller. For instance, and withoutlimitation, a controller may control at least a parameter of theelectrical charging current. For example, in some cases, controller maycontrol one or more of current (Amps), potential (Volts), and/or power(Watts) of electrical charging current by way of control signal. In somecases, controller may be configured to selectively engage electricalcharging current, for example ON or OFF by way of control signal.

With continued reference to FIG. 1 , charging component 132 may besupplied by battery storage unit 176. A “battery storage unit,” for thepurposes of this disclosure, refer to a device or station that mayinclude a plurality of batteries to be used to store electrical energy.In a non-limiting embodiment, battery storage unit 176 may be a part ofcharging component 132. In another non-limiting embodiment, batterystorage unit 176 may be located in a remote location relative tocharging component 132 wherein charging component 132 may charge thebattery pack of electric aircraft 152 using the power stored in batterystorage unit 176. For instance and without limitation, battery storageunit 176 may be consistent with the battery storage system in U.S.patent application Ser. No. 17/373,863 and titled, “SYSTEM FOR CHARGINGFROM AN ELECTRIC VEHICLE CHARGER TO AN ELECTRIC GRID,” which isincorporated in its entirety herein. Any electrical device and/orelectrical vehicle may be charged from a power source such as batterystorage unit 176.

With continued reference to FIG. 1 , charging component 132 and/orhousing of connector may include fastener 144. As used in thisdisclosure, a “fastener” is a physical component that is designed and/orconfigured to attach or fasten two (or more) components together.Charging component 132 may include one or more attachment components ormechanisms, for example without limitation fasteners, threads, snaps,canted coil springs, and the like. In some cases, connector may beconnected to port by way of one or more press fasteners. As used in thisdisclosure, a “press fastener” is a fastener that couples a firstsurface to a second surface when the two surfaces are pressed together.Some press fasteners include elements on the first surface thatinterlock with elements on the second surface; such fasteners includewithout limitation hook-and-loop fasteners such as VELCRO fastenersproduced by Velcro Industries B.V. Limited Liability Company of CuracaoNetherlands, and fasteners held together by a plurality of flanged or“mushroom”-shaped elements, such as 5M DUAL LOCK fasteners manufacturedby 5M Company of Saint Paul, Minnesota Press-fastener may also includeadhesives, including reusable gel adhesives, GECKSKIN adhesivesdeveloped by the University of Massachusetts in Amherst, of Amherst,Massachusetts, or other reusable adhesives. Where press-fastenerincludes an adhesive, the adhesive may be entirely located on the firstsurface of the press-fastener or on the second surface of thepress-fastener, allowing any surface that can adhere to the adhesive toserve as the corresponding surface. In some cases, connector may beconnected to port by way of magnetic force. For example, connector mayinclude one or more of a magnetic, a ferro-magnetic material, and/or anelectromagnet. Fastener 144 may be configured to provide removableattachment between charging component 132 and at least a port, forexample electric aircraft port 156. As used in this disclosure,“removable attachment” is an attributive term that refers to anattribute of one or more relata to be attached to and subsequentlydetached from another relata; removable attachment is a relation that iscontrary to permanent attachment wherein two or more relata may beattached without any means for future detachment. Exemplary non-limitingmethods of permanent attachment include certain uses of adhesives,glues, nails, engineering interference (i.e., press) fits, and the like.In some cases, detachment of two or more relata permanently attached mayresult in breakage of one or more of the two or more relata.

With continued reference to FIG. 1 , charging component 132 may includea charger. A “charger,” for the purposes of this disclosure, refers toan electric device that serves as a medium to provide electricity to abattery by a charge connection. The charger may include, but not limitedto, a constant voltage charger, a constant current charger, a tapercurrent charger, a pulsed current charger, a negative pulse charger, adumb charger, a fast charger, a smart charger, an IUI charger, abidirectional charger, a trickle charger and/or a float charger. In anon-limiting embodiment, a recharging station may be configured tosupport bidirectional charging as a function of the charger.Bidirectional charging may include the transfer of electrical energythat goes two ways: from an electric grid to an EV battery or from an EVbattery to an electric grid. In a non-limiting embodiment, chargingstation may perform bidirectional charging via the connection betweencharging component 132 and electric aircraft port 156. In a non-limitingembodiment, charging station may automatically connect the charger toelectric aircraft port 156. In a non-limiting embodiment, the charger ismechanically coupled to a docking terminal and protruded outward for auser to manually adjust and connect to electric aircraft port 156 ofelectric aircraft 152. In a non-limiting embodiment, the charger maylock itself via the charging station if the connection between electricaircraft 152 and charging component 132 is not formed or detected. Forinstance, the charger may be configured to remain locked and unusableunless an electric aircraft nearby requires charging and forms a chargeconnection. In a non-limiting embodiment, the charger may be unlocked toallow for use in the charging of an electric aircraft or the receivingof electric power from the electric aircraft when a charge connection isdetected and/or formed. In a non-limiting embodiment, charger mayincorporate a timer that is configured to allow for an electric aircraftto use the charger for the duration of the timer. For instance, once acharge connection is detected and/or formed and the electric aircraft isphysically linked with the charger, a timer may begin to countdown inwhich the aircraft may utilize the charger before the timer runs out andthe charger becomes locked. A person of ordinary skill in the art, afterviewing the entirety of this disclosure, would appreciate the variouscharging capabilities that may be conducted.

With continued reference to FIG. 1 , charging component 132 may includea power converter. As used in this disclosure, a “power converter” is anelectrical system and/or circuit that converts electrical energy fromone form to another. For example, in some cases power converter mayconvert alternating current to direct current, and/or direct current toalternating current. In some cases, power converter may convertelectrical energy having a first potential to a second potential.Alternative or additionally, in some cases, power converter may convertelectrical energy having a first flow (i.e., current) to a second flow.As used in this disclosure, an “alternating current to direct currentconverter” is an electrical component that is configured to convertalternating current to digital current. An alternating current to directcurrent (AC-DC) converter may include an alternating current to directcurrent power supply and/or transformer. In some cases, the AC-DCconverter may be located within an electric aircraft 104 and conductorsmay provide an alternating current to the electric aircraft by way of atleast a charger. Alternatively and/or additionally, in some cases, AC-DCconverter may be located outside of electric vehicle and an electricalcharging current may be provided as a direct current to electricaircraft 152, by way of at least a charger. In some cases, AC-DCconverter may be used to recharge the battery pack of electric aircraft152. In some embodiments, power converter may have a connection to agrid power component, for example by way of at least a charger. Gridpower component may be connected to an external electrical power grid.In some embodiments, grid power component may be configured to slowlycharge one or more batteries in order to reduce strain on nearbyelectrical power grids. In one embodiment, grid power component may havean AC grid current of at least 250 amps. In some embodiments, grid powercomponent may have an AC grid current of more or less than 250 amps. Inone embodiment, grid power component may have an AC voltage connectionof 280 Vac. In other embodiments, grid power component may have an ACvoltage connection of above or below 280 Vac. In some embodiments,charging station may provide power to the grid power component by theelectric energy stored in its own battery pack of charging component 132or the battery pack of an electric aircraft. In this configuration,charging station may provide power to a surrounding electrical powergrid.

With continued reference to FIG. 1 , in some cases, the power convertermay include one or more direct current to direct current (DC-DC)converters. DC-DC converters may include without limitation any of alinear regulator, a voltage regulator, a motor-generator, a rotaryconverter, and/or a switched-mode power supply. In some cases, powerconverter may include a direct current to alternating current (DC-AC)converter. DC-AC converters may include without limitation any of apower inverter, a motor-generator, a rotary converter, and/or aswitched-mode power supply. In some cases, power converter may includeone or more alternating current to direct current (AC-DC) converters.AC-DC converters may include without limitation any of a rectifier, amains power supply unit (PSU), a motor-generator, a rotary converter,and/or a switched-mode power supply. In some cases, power converter mayinclude one or more alternating current to alternating current (AC-AC)converters. AC-AC converters may include any of a transformer,autotransformer, a voltage converter, a voltage regulator, acycloconverter, a variable-frequency transformer, a motor-generator, arotary converter, and/or a switched-mode power supply. In some cases,power converter may provide electrical isolation between two or moreelectrical circuits, for example battery pack 116 and charger. In somecases, power converter may provide a potential (i.e., voltage) step-downor step-up. In some embodiments, power converter may receive analternating current and output a direct current. In some embodiments,power converter may receive a potential within a range of about 100Volts to about 500 Volts. In some embodiments, power converter mayoutput a potential within a range of about 200 Volts to about 600 Volts.In some embodiments, power converter may receive a first potential andoutput a second potential at least as high as the first potential. Insome embodiments, power converter may be configured to receive a firstcurrent from a power source including a “Level 2” charger, such that thefirst current consists of an alternating current having a potential ofabout 240 Volts or about 120 Volts and a maximum current no greater thanabout 30 Amps or no greater than about 20 Amps. In some embodiments,power converter may be configured to output a second current which iscomparable to that output by a “Level 5” charger, such that the secondcurrent consists of a direct current having a potential in a rangebetween about 200 Volts and about 600 Volts.

With continued reference to FIG. 1 , charging component 132 may includeone or more conductors configured to conduct, for example, a directcurrent (DC) or an alternating current (AC), and the like thereof. In anon-limiting embodiment, the conductor may be configured to charge orrecharge, for example, the battery pack of the electric aircraft. Asused in this disclosure, a “conductor” is a component that facilitatesconduction. As used in this disclosure, “conduction” is a process bywhich one or more of heat and/or electricity is transmitted through asubstance, for example when there is a difference of effort (i.e.,temperature or electrical potential) between adjoining regions. In somecases, a conductor may be configured to charge and/or recharge anelectric vehicle. For instance, conductor may be connected to thebattery pack of electric aircraft 152 and/or battery storage unit 160 ofcharging component 132. The conductor may be designed and/or configuredto facilitate a specified amount of electrical power, current, orcurrent type. For example, a conductor may include a direct currentconductor. As used in this disclosure, a “direct current conductor” is aconductor configured to carry a direct current for recharging thebattery pack of electric aircraft 152. As used in this disclosure,“direct current” is one-directional flow of electric charge. In somecases, a conductor may include an alternating current conductor. As usedin this disclosure, an “alternating current conductor” is a conductorconfigured to carry an alternating current for recharging the batterypack of electric aircraft 152. As used in this disclosure, an“alternating current” is a flow of electric charge that periodicallyreverse direction; in some cases, an alternating current may change itsmagnitude continuously with in time (e.g., sine wave). In a non-limitingembodiment, charging component 132 may include a ground conductor. A“ground conductor,” for the purpose of this disclosure, is a conductoror a system or that is intentionally grounded. In a non-limitingembodiment, the ground conductor may include any suitable conductorconfigured to be in electrical communication with a ground. In anon-limiting embodiment, a ground is a reference point in an electricalcircuit, a common return path for electric current, or a direct physicalconnection to the earth. The ground may include an absolute ground suchas earth or ground may include a relative (or reference) ground, forexample in a floating configuration. The ground conductor functions toprovide a grounding or earthing path for any abnormal, excess or strayelectricity. In a non-limiting embodiment, charging component 132 mayinclude a control signal conductor configured to conduct a controlsignal. A “control signal conductor,” for the purpose of thisdisclosure, is a conductor configured to carry a control signal betweencharging component 132 and computing device 112. The control signal isan electrical signal that is indicative of information. The controlsignal may include, for example, an analog signal, a digital signal, orthe like.

With continued reference to FIG. 1 , sensor 104 may recognize that acharging connection has been created between charging component 132 andelectric aircraft 152 and its electric aircraft port 156 thatfacilitates communication between charging component 132 and electricaircraft 152. For example, and without limitation, sensor 104 mayidentify a change in current through a charging connector of chargingcomponent 132, indicating the charging connector is in electriccommunication with, for example, a port of electric aircraft 152, asdiscussed further below. For the purposes of this disclosure, a“charging connection” is a connection associated with charging a powersource, such as, for example, a battery. The charging connection may bea wired or wireless connection, as discussed further below in thisdisclosure. The charging connection may include a communication betweencharging component 132 and electric aircraft 152. For example, andwithout limitation, one or more communications between chargingcomponent 132 and electric aircraft 152 may be facilitated by thecharging connection. As used in this disclosure, “communication” is anattribute where two or more relata interact with one another, forexample, within a specific domain or in a certain manner. In some cases,communication between two or more relata may be of a specific domain,such as, and without limitation, electric communication, fluidiccommunication, informatic communication, mechanic communication, and thelike. As used in this disclosure, “electric communication” is anattribute wherein two or more relata interact with one another by way ofan electric current or electricity in general. For example, and withoutlimitation, a communication between charging component 132 and electricaircraft 152 may include an electric communication. As used in thisdisclosure, a “fluidic communication” is an attribute wherein two ormore relata interact with one another by way of a fluidic flow or fluidin general. For example, and without limitation, a coolant may flowbetween charging component 132 and electric aircraft 152 when there is acharging connection between charging component 132 and electric aircraft152. As used in this disclosure, “informatic communication” is anattribute wherein two or more relata interact with one another by way ofan information flow or information in general. As used in thisdisclosure, “mechanic communication” is an attribute wherein two or morerelata interact with one another by way of mechanical means, forinstance mechanic effort (e.g., force) and flow (e.g., velocity). In oneor more embodiments, communication of the charging connection mayinclude various forms of communication. For example, and withoutlimitation, an electrical contact without making physical contact, forexample, by way of inductance, may be made between charging component132 and electric aircraft 152 to facilitate communication. Exemplaryconductor materials include metals, such as without limitation copper,nickel, steel, and the like. In one or more embodiments, a contact ofcharging component 132 may be configured to provide electricalcommunication with a mating component within a port of electric aircraft152. In one or more embodiments, contact may be configured to mate withan external connector. As used in this disclosure, a “chargingconnector” is a distal end of a tether or a bundle of tethers, e.g.,hose, tubing, cables, wires, and the like, which is configured toremovably attach with a mating component, for example without limitationa port. As used in this disclosure, a “port” is an interface for exampleof an interface configured to receive another component or an interfaceconfigured to transmit and/or receive signal on a computing device. Forexample, in the case of an electric vehicle port, the port interfaceswith a number of conductors and/or a coolant flow path by way ofreceiving a connector. In the case of a computing device port, the portmay provide an interface between a signal and a computing device. Aconnector may include a male component having a penetrative form andport may include a female component having a receptive form, receptiveto the male component. Alternatively or additionally, connector may havea female component and port may have a male component. In some cases,connector may include multiple connections, which may make contactand/or communicate with associated mating components within port, whenthe connector is mated with the port.

With continued reference to FIG. 1 , sensor 104 may be configured totransmit any datum detected such as, but not limited to, residual datum108, to computing device 112. In a non-limiting embodiment, computingdevice 112 may be connected to a network. A “network, for the purpose ofthis disclosure, is any medium configured to facilitate communicationbetween two or more devices. The network may include, but not limitedto, an artificial neural network, wireless network, radio network,electrical network, broadcast network, and the like thereof. In anon-limiting embodiment, the network may be a public network in whichany electric aircraft that may fly within its range may be informed ofthe recharging station. In another non-limiting embodiment, a pluralityof electric aircrafts that fly within the range of the network may beaware of each other's location and communicate via the network using anymeans of connection such as Wi-Fi, Bluetooth, radio transmission, andthe like thereof. In a non-limiting embodiment, the network may be aprivate network in which the electric aircraft must request access toconnect to the network and access the recharging station or otherelectric aircrafts that are within the network. In a non-limitingembodiment, the network may include a mesh network. The mesh network mayinclude an avionic mesh network. The mesh network may include, withoutlimitation, an avionic mesh network. For instance and withoutlimitation, the avionic mesh network may be consistent with the avionicmesh network in U.S. patent application Ser. No. 17/348,916 and titled“METHODS AND SYSTEMS FOR SIMULATED OPERATION OF AN ELECTRIC VERTICALTAKE-OFF AND LANDING (EVTOL) AIRCRAFT,” which is incorporated herein byreference in its entirety. In some embodiments, the network may includean intra-aircraft network and/or an inter-aircraft network.Intra-aircraft network may include any intra-aircraft network describedin this disclosure. Inter-aircraft network may include anyinter-aircraft network described in this disclosure. In some cases, thenetwork may communicate encrypted data. As used in this disclosure,“encrypted data” is any communicable information that is protected orsecured by any method, including obfuscation, encryption, and the like.Encrypted data may include information protected by any cryptographicmethod described in this disclosure. In some embodiments, the networkmay include an intra-aircraft network and/or an inter-aircraft network.Intra-aircraft network may include any intra-aircraft network describedin this disclosure. Inter-aircraft network may include anyinter-aircraft network described in this disclosure. In a non-limitingembodiment, computing device 112 may receive datum from an airborneelectric aircraft that is connected to the network and/or within therange of the network. For example and without limitation, electricaircraft 152 that comes within the range of the network may digitallytransmit data about the aircraft and its battery recharging needs. Thisis so, at least in part, for computing device 112 to generate securitymeasure 120 in advanced before the occurrence of alert datum 124.Persons skilled in the art, upon reviewing the entirety of thisdisclosure, will be aware of the various digital communication andtransmissions used for the purpose described herein.

With continued reference to FIG. 1 , computing device 112 may beconfigured to receive residual datum 108. In a non-limiting embodiment,computing device 112 may include one or more circuit elements, computingdevices, FGPAs, or other electronic devices. Any module as describedherein, may be created using any combination of hardware and/or softwarelogic commands, and may be physically or conceptually separate from ormerged with any other such module, as persons skilled in the art willappreciate upon reviewing the entirety of this disclosure. In anon-limiting embodiment, computing device 112 may include a plurality ofphysical controller area network buses, wherein the plurality ofphysical controller area network buses are communicatively connected tocomputing device 112. In a non-limiting embodiment, electric aircraft152 may include a plurality of physical controller are network busescommunicatively connected to electric aircraft 152. A “physicalcontroller area network bus,” as used in this disclosure, is vehicle busunit including a central processing unit (CPU), a CAN controller, and atransceiver designed to allow devices to communicate with each other'sapplications without the need of a host computer which is locatedphysically at the aircraft. For instance and without limitation, thephysical controller area network bus unit may be consistent with thephysical controller are network bus unit in U.S. patent application Ser.No. 17/218,342 and titled, “METHOD AND SYSTEM FOR VIRTUALIZING APLURALITY OF CONTROLLER AREA NETWORK BUS UNITS COMMUNICATIVELY CONNECTEDTO AN AIRCRAFT,” which is incorporated herein in its entirety. In anon-limiting embodiment, the Physical controller area network (CAN) busunit may include physical circuit elements that may use, for instanceand without limitation, twisted pair, digital circuit elements/FGPA,microcontroller, or the like to perform, without limitation, processingand/or signal transmission processes and/or tasks; circuit elements maybe used to implement CAN bus components and/or constituent parts asdescribed in further detail below. A plurality of physical CAN bus unitsmay be located physically at electric aircraft 152 and/or computingdevice 112, wherein the hardware of the physical CAN bus unit may beintegrated within the infrastructure of electric aircraft 152 and/orcomputing device 112. In an embodiment, communicative connectionincludes electrically coupling an output of one device, component, orcircuit to an input of another device, component, or circuit.Communicative connecting may be performed via a bus or other facilityfor intercommunication between elements of a computing device.Communicative connecting may include indirect connections via “wireless”connection, low power wide area network, radio communication, opticalcommunication, magnetic, capacitive, optical coupling, or the like. Thephysical CAN bus units may be mechanically connected to each otherwithin the aircraft wherein the physical infrastructure of the device isintegrated into the aircraft for control and operation of variousdevices within the electric aircraft 152 and/or computing device 112.The physical CAN bus unit may be communicatively connected with eachother and/or to one or more other devices, such as via a CAN gateway.Communicatively connecting may include direct electrical wiring, such asis done within automobiles and aircraft. Communicatively connecting mayinclude infrastructure for receiving and/or transmitting transmissionsignals, such as with sending and propagating an analogue or digitalsignal using wired, optical, and/or wireless electromagnetictransmission medium.

With continued reference to FIG. 1 , computing device 112 may beconfigured to identify a residual element 116 as a function of residualdatum 108. A “residual element,” for the purpose of this disclosure, isany instance within a collection of data that may represent anabnormality of an electric current. In a non-limiting embodiment,residual element 116 may include any moment that may be hazardous to anyequipment and/or infrastructure involved in any charging process. Forexample and without limitation, residual element 116 may include anelectrical abnormality. An “electrical abnormality,” for the purpose ofthis disclosure, is any fault or fault current associated with at leastan electric current. For example and without limitation, the electricalabnormality may include a short circuit which may include a fault inwhich a live wire touches a neutral or ground wire. This may be detectedin an event a circuit is interrupted by a failure of a current-carryingwire (phase or neutral) or a blown fuse or circuit breaker. Inthree-phase systems, a fault may involve one or more phases and ground,or may occur only between phases. In a non-limiting embodiment, residualelement 116 may include an electrical fault, transient fault, persistentfault, asymmetric fault, symmetric fault, bolted fault, arcing fault,and the like thereof. Persons skilled in the art, upon reviewing theentirety of this disclosure, will be aware of the various embodiments offaults that may be detected for purposes as described herein.

With continued reference to FIG. 1 , residual element 116 may include aresidual current. A “residual current,” for the purpose of thisdisclosure, an electric current that continues to flow in an electricaldevice when there is no voltage supply. In a non-limiting embodiment,the residual current may include a leakage current. A “leakage current,”for the purpose of this disclosure, a current which flows throughprotective ground conductor to ground. In the absence of grounding orimproper grounding connections, it is the current that could flow fromany conductive part or the surface of non-conductive parts to ground ifany conductive path was available (i.e. human body). In a non-limitingembodiment, the leakage current may include an AC leakage current and/ora DC leakage current. In a non-limiting embodiment, sensor 104 maycapture an instance of an AC leakage current in the event a parallelcombination of capacitance and DC resistance between a Voltage source(ac line) and the grounded conductive parts of an electrical device,such as, but not limited to, charging component 132, electric aircraft152, battery pack 160, and/or battery storage unit 176, is detected. Inanother non-limiting embodiment, sensor 104 may detect a DC leakagecaused by the DC resistance usually is insignificant compared to the acimpedance of various parallel capacitances. The capacitance may beintentional (such as in EMI filter capacitors) or unintentional. Someexamples of unintentional capacitances are spacings on printed wiringboards, insulations between semiconductors and grounded heat sinks, andthe primary-to-secondary capacitance of isolating transformers withinthe power supply. In a non-limiting embodiment, the residual current mayinclude a fault current. A “fault current,” for the purpose of thisdisclosure, is a current flowing to earth due to an insulation fault. An“insulation fault,” for the purpose of this disclosure, is a faultwithin the insulation materials used in an electrical device such ascharging component 132, electric aircraft 152, battery pack 160, batterystorage unit 176, etc. In a non-limiting embodiment, the fault currentmay arise due to defective insulation between live conductors and flowsback to ground. Even if a person directly touches a live conductor, thefault current flows to ground. An upstream RCD detects this faultcurrent and immediately disconnects the circuit. In another non-limitingembodiment, the fault current may include an unintended, uncontrolled,high current flow through any electrical system. For example and withoutlimitation, fault currents are caused by very low impedance shortcircuits. These may be shorts to ground or across phases. The resultinghigh current flow can result in overheating of equipment and conductors,excesses forces, and at times even serious arcs, blasts, and explosions.Persons skilled in the art, upon reviewing the entirety of thisdisclosure, will be aware of the various embodiments of a residualcurrent and the causes for purposes as described herein.

Still referring to FIG. 1 , residual element 116 may include, a shortcircuit, an electric overcharge, an electric undercharge, and the likethereof. In another non-limiting example, residual element 116 mayinclude an unsafe amount of water and/or level of wetness on any surfaceor electrical part of charging component 132 and/or electric aircraftport 156. Computing device 112 may analyze residual datum 108 andisolate residual element 116 which may represent a potential faultand/or hazard to a charging process. In a non-limiting embodiment,residual element 116 may not be any serious fault within the electriccomponents of charging component 132 and/or electric aircraft 152. Forexample and without limitation, computing device 112 may isolate arelatively high impedance compared to normal operating levels of system100, which may be well understood by a person of ordinary skill in theart, but may not result in any significant damage. In a non-limitingembodiment, computing device 112 may isolate residual element 116 usingthermal overload relay 148, in which the thermal overload may be eithertoo high or low, indicating an unusual thermal event. Persons skilled inthe art, upon reviewing the entirety of this disclosure, will be awareof the various potential electrical and thermal phenomenon which may beanalyzed for purposes as described herein.

Still referring to FIG. 1 , computing device 112 may be configured todetermine alert datum 124 as a function of the identification ofresidual element 116. For purposes of this disclosure, an “alert datum”is an element of information regarding a determination of a residualcurrent, present-time failure, fault, or degradation of a condition orworking order of any component and/or connection associated with thecharging process, charging component 132, and/or electric aircraft 152.In one or more embodiments, alert datum 124 may be determined as afunction of residual datum 108, as discussed further in this disclosure.In some embodiment, computing device 112 may be configured to disableany charging connection based on alert datum 124. In a non-limitingembodiment, alert datum 124 may denote any disconnection betweencharging component 132 and electric aircraft 152. For example andwithout limitation, the disconnection may include any electricaldisconnection and/or mechanical disconnection. In a non-limitingembodiment, alert datum 124 may include the presence of one or moreunsecure connection, wherein the unsecure connection may include a looseand/or faulty connection. For example and without limitation, theconnection may include a coupling of a charging port attached toelectric aircraft 152 such as electric aircraft port 156 and chargingcomponent 132. For example and without limitation, an inappropriatelydisabled connection may include turning off the charging system and/orcharging component 132 when not supposed to, such as in the middle of acharging process. Persons skilled in the art, upon reviewing theentirety of this disclosure, will be aware of the various embodiments ofa disconnection for purposes as described herein.

With continued reference to FIG. 1 , computing device 112 may beconfigured to generate a residual prediction datum as a function of theidentification of residual element 116. A “residual prediction datum,”for the purpose of this disclosure, is one or more elements of datagenerated by the computing device 112 that represents an expectedresidual output or range of residual outputs associated with residualelement 116. The residual prediction datum may constantly be generatedby computing device 112 adjusting for any variations detected in acharging process for electric aircraft 152. In a non-limitingembodiment, computing device 112 may be configured to compare residualelement 116 and the residual prediction datum for generating alert datum124. Computing device 112 may be configured to compare residual element116 and the residual prediction datum utilizing subtraction. Innon-limiting embodiments, subtraction may include subtracting residualelement 116 from the residual prediction datum. In non-limitingembodiments, subtraction may include subtracting the residual predictiondatum from residual element 116. Computing device 112 may be configuredto compare residual element 116 and the residual prediction datumutilizing ratios. In non-limiting embodiments, ratios may include theratio of residual datum 116 to the residual prediction datum. Innon-limiting embodiments, ratios may include the ration of the residualprediction datum to residual datum 116. Computing device 112 may beconfigured to compare residual datum 116 and the residual predictiondatum utilizing addition. In non-limiting embodiments, addition mayinclude adding residual datum 116 and the residual prediction datum andcomparing the total to a predetermined threshold datum. The comparisonmay take place at one point in a flight envelope, constantly withadjusted detected readings and predictions, at regular intervals, whencommanded to do so by a pilot, user, or computer, or a combinationthereof. In a non-limiting embodiment, computing device 112 may generatealert datum 124 as a function of the comparison. In a non-limitingembodiment, computing device 112 may be configured to compare residualdatum 116 and the residual prediction datum at regular intervals such asevery second, every minute, every five minutes, or at a predeterminedtime interval as a function of timer module 172.

With continued reference to FIG. 1 , alert datum 124 may include anynotification such as previous detections of residual datum, comparisonsbetween the most recent detection with previous detections, textualoutput, audio output, and any other output configured to warn a user orrelay information to a user. In a non-limiting embodiment, alert datum124 may include a warning, wherein the warning is configured to informone or more users of residual element 116. A “warning,” for the purposeof this disclosure, is any sign indicating an instance of a residualcurrent to be resolved. For example and without limitation, the warningmay include an auditory siren incorporated with an automated messageinforming users of the identification of residual element 116. Thewarning may include any warning as to be well understood by personsskilled in the art, upon reviewing the entirety of this disclosure. In anon-limiting embodiment, alert datum 124 may be generated as a functionof residual threshold 164

Still referring to FIG. 1 , computing device 112 may be configured todetermine alert datum 124 as a function of residual threshold 164. A“residual threshold,” for the purpose of this disclosure, is a set ofvalues that determine if a residual element 116 is above, below, orwithin a range denoting a significant disruptive phenomenon such asalert datum 124. In a non-limiting embodiment, residual threshold 164may be used to verify if an identified residual element 116 is a realinstance of a leakage. For example and without limitation, sensor 104may detect a temperature of battery pack 160 wherein the values ofresidual threshold 164 may include to be between 15 and 35 degreesCelsius, wherein the 15 degrees Celsius and the 35 degrees Celsiusvalues represent the cutoff for the temperature to fall outside of todenote alert datum 124. For example and without limitation, the chargingprocess may include a long process in which a moment and/or instancecaptured wherein the temperature triggers computing device 112 toidentify residual element 116 representing the temperature is not afluke. A “fluke,” for the purpose of this disclosure, is a residualelement 116 wherein an element of data indicates an outlier fallingoutside the residual threshold 164. In another non-limiting embodiment,residual threshold 164 may include lower and upper limits such as 5 mAand 500 mA, respectively. In the event residual element 116 including aleakage current falls between the upper and lower limits, computingdevice 112 may not generate alert datum 124 and/or execute securitymeasure 120. In an embodiment, computing device 112 may continuouslymeasure if residual element 116 stays inside the lower and upper limitsto verify that the instance of residual element 116 is not indicative ofa serious threat. Residual leakage currents are commonly present inelectrical devices, but they are not always dangerous so computingdevice 112 may be configured to monitor such parameters to deducewhether or not the instance of a leakage is a fluke or a real threatPersons skilled in the art, upon reviewing the entirety of thisdisclosure, will be aware of the various embodiments and signs ofresidual currents and possible outcomes for purposes as describedherein.

With continued reference to FIG. 1 , in a non-limiting embodiment,computing device 112 may be configured to analyze residual element 116using timer module 172 in order to determine if residual element 116 isan alert datum 124. With continued reference to FIG. 1 , a “timermodule,” for the purpose of this disclosure, is a timing device, is atiming device configured to track the time taken of an occurrence orcountdown in the event of an occurrence. In a non-limiting embodiment,timer module 172 may include a watchdog timer. In a non-limitingembodiment, timer module 172 may include an oscillator such as a crystaloscillator or cesium oscillator, wherein the oscillator may beconfigured to generate and/or use a clock signal. Timer module 172 mayinclude a counter, wherein the counter is configured to count the numberof instances of, but not limited to, rising edges, falling edges, and/orchanges of a clock signal, and the like thereof. In a non-limitingexample, alert datum 124 may include an inappropriate connection betweencharging component 132 and electric aircraft port 156, in which sensor104 detects the improper connection. The connection may be establishedas a function of a human operator or automated operator. In anon-limiting embodiment, alert datum 124 may include a minor improperconnection wherein no potential risk of damage to any component ispresent, wherein computing device 112 may generate security measure 120using timer module 172, wherein timer module may start a timer of 30seconds until security measure 120 is initiated. The 30 seconds isprovided in order to give an operator ample time to fix the improperconnection. In the event alert datum 124 is not resolved by the time thetimer of timer module 172 expires, computing device 112 may initiatesecurity measure 120, which may include residual priority command 128.An “residual priority command,” for the purpose of this disclosure, isan immediate shutting down of charging related electrical components. Ina non-limiting embodiment, residual priority command 128 may include theactivation of a siren or alert to indicate a priority situation to beresolved. In a non-limiting embodiment, residual priority command 128may include electrically disabling all components of charging component132. For example and without limitation, computing device 112 mayimmediately shut down all charging processes in the event residualpriority command 128 is initiated. Persons skilled in the art, uponreviewing the entirety of this disclosure, will be aware of the variousseverity of emergencies and protocols designed to respond to them forpurposes as described herein.

With continued reference to FIG. 1 , generating alert datum 124 mayinclude cutting the power transmitted to battery pack 160 based onreceiving residual datum 108 and/or residual element 116. If a batterymodule of battery pack 160 is electrically connected to a neighboringbattery module, controller may cut or divert the electrical connectionbetween the neighboring battery module and the battery module to preventdamage to the neighboring battery module.

With continued reference to FIG. 1 , computing device 112 may train afirst machine-learning model as a function of a fault detection trainingset, wherein the first machine-learning model may be configured tooutput alert datum 124 using residual element 116 as an input. Thetraining set may correlate any past instances of residual element 116detected from previous instances in which alert datum 124 have beendetermined and security measure 120 has been generated/initiated. In anon-limiting embodiment, computing device 112 may identify residualelement 116 and determine the correct alert datum based on the trainingset that best correlates the inputted residual element 116 to an alertdatum retrieved from the database. The training set may be used as aninput for a machine-learning algorithm which may be used by themachine-learning model to output alert datum 124, which is adetermination that residual element 116 is an alert datum 124. In anon-limiting embodiment, computing device 112 may train a secondmachine-learning model using a disruption training set, wherein thesecond machine-learning model is configured to output security measure120 using alert datum 124 as an input. In a non-limiting embodiment,computing device 112 may determine alert datum 124 and generate and/orassociate the correct security measure based on the residual trainingset that best correlates the inputted alert datum 124 to a securitymeasure 120 retrieved from the database. The residual training set maybe used as an input for a second machine-learning algorithm which may beused by the machine-learning model to output security measure 120.Persons skilled in the art, upon reviewing the entirety of thisdisclosure, will be aware of the various embodiments of machine-learningfor purposes as described herein.

With continued reference to FIG. 1 , computing device may be configuredto generate security measure 120 as a function of alert datum 124. In anon-limiting embodiment, computing device may be configured to executesecurity measure 120 as a function of alert datum 124 and/or timermodule 172. In one or more embodiments, alert datum 124 may indicatebattery pack 160 of electric aircraft 152 and/or battery storage unit176 of charging component 132, is operating outside of an acceptableoperation condition represented by a threshold such as fault threshold164. In a non-limiting embodiment, fault threshold 164 may be used toinitiate a specific reaction of computing device 112 such as securitymeasure 120. The threshold may be set by, for example, a user orcomputing device 112 based on, for example, prior use or an input. Forexample, and without limitation, computing device 112 may indicate thatbattery pack 160 of electric aircraft 152 and/or battery storage unit176 of charging component 132 has a current of 350 mA. Such a currentmay be outside of a preconfigured threshold of an upper limit of, forexample, 300 mA of an operational condition, such as current, of abattery pack 160 and/or battery storage unit 176 and thus the chargingconnection may be disabled by computing device 112 to preventovercharging and any further leakage to battery pack 160 of electricaircraft 152 and/or battery storage unit 176. For the purposes of thisdisclosure, a “security measure” is a signal transmitted and/or to beinitiated to electric aircraft 152 and/or charging component 132 in aresponse to alert datum 124, wherein the response is an electricalturnoff of any electric switch of any electrical components involved inthe charging process. In a non-limiting embodiment, security measure 120may include a plurality of security measures 120. For example andwithout limitation, computing device 112 may generate the plurality ofsecurity measures based on the level of severity of residual element 116and/or as a function of residual threshold 164. In a non-limitingembodiment, security measure 120 may include a protocol in whichcomputing device 112 is configured to provide instructions and/or acommand to disable and/or terminate any switch and/or chargingconnection between electric aircraft 152 and/or electric aircraft port156 and charging component 132. “Executing,” for the purpose of thisdisclosure, is transmitting a signal to triggering the process ofsecurity measure 120, including one or more instructions for thecompletion and/or execution of the process. In a non-limitingembodiment, security measure 120 may eliminate one or more connectionsfrom charging component 132 to any port. For example, and withoutlimitation, security measure 120 may eliminate one or more secureconnections, unsecure connections, loose connections, faultyconnections, and the like thereof by any means of disconnection. In anon-limiting embodiment, computing device 112 may initiate, execute,and/or perform security measure 120 automatically. In a non-limitingexample, security measure 120 may include one or more physicaldisconnections such as removing one or more charging connectors and/orplugs from any port. In another non-limiting example, security measure120 may include one or more electrical disconnections such aseliminating one or more circuits and/or current feeds from the chargingconnector, electric aircraft port 156, charging component 132, and/orelectric aircraft 152. Security measure 120 may include disabling anyelectrical connection associated with charging, wherein disabling mayinclude disabling the charging connection, terminating a communicationbetween electric aircraft 152 and charging component 132. For example,and without limitation, disabling the charging connection may includeterminating a power supply to charging component 132 so that chargingcomponent 132 is no longer providing power to electrical aircraft 152.In another example, and without limitation, disabling the chargingconnection may include terminating a power supply to electric aircraft152. In another example, and without limitation, disabling the chargingconnection may include using a relay or switch between chargingcomponent 132 and electric aircraft 152 to terminate charging connectionand the charging of between charging component 132 and electric aircraft152.

With continued reference to FIG. 1 , security measure 120 may include aset of instructions that an operator or a plurality of operators mayundertake to resolve residual element 116. For example and withoutlimitation, security measure 120 may include disconnecting all portsassociated with charging between electric aircraft 152 and chargingcomponent 132, by means of physical human maneuvers. In the event suchmeasures are not undertaken or not undertaken within a specific timelimit set by timer module 172, residual priority command 128 may beinitiated, wherein any charging connectors are blocked by any lockingmechanism within charging component 132. In a non-limiting embodiment,the locking mechanism may be controlled as a function of a safety lockinstruction which may be a part of security measure 120. A “safety lockinstruction,” for the purpose of this disclosure, is a safety featureand an operational direction or implementation for charging component132 and any locking mechanism it may have. In a non-limiting embodiment,the safety lock instruction may include a feature that may control,whether or not charging (or current flow) should be enabled, disabled,modified, regulated, or the like. For example and without limitation,the safety lock instruction include an initial security measure toverify a physical connection between charging component 132 and electricaircraft 152 and/or electric aircraft port 156 is established. Inanother non-limiting example, the safety lock instruction may include afeature that ensures no current flow is occurring between chargingcomponent 132 and electric aircraft 152 or electric aircraft port 156.The safety lock instruction may include specific instructions that mayinstruct any locking mechanism within charging component 132 to blockany transfer of electrical energy between charging component 132 andelectric aircraft 152. For example and without limitation, the safetylock instruction may include instructions for computing device 112and/or charging component 132, which may be electrically connected withcomputing device 112, to lock fastener 144 to ensure no flow ofelectrical energy is occurring as long as charging component 132 is notmated with electric aircraft 152 and/or electric aircraft port 156. In anon-limiting embodiment, computing device 112 and/or charging component132 may unlock fastener 144 to ensures that there is a flow ofelectrical energy between charging component 132 and electric aircraftport 156. In a non-limiting embodiment, the safety lock instruction mayinclude a feature that ensure fastener 144 fastener is lockedindefinitely without interruption, until the performance of the charginginstruction is complete. In another non-limiting example, the safetylock instruction may include unlocking fastener 144 in order todisconnect any charging connectors and/or cables from charging component132 and/or electric aircraft port 156. Persons skilled in the art, uponreviewing the entirety of this disclosure, will be aware of the varioussafety features for controlling a fastener for purposes as describedherein.

With continued reference to FIG. 1 , a charging connection may beinterrupted abruptly by an outside factor such as a user or an accident,wherein computing device 112 may initiate a residual priority command128. A “residual priority command,” for the purpose of this disclosure,is any security measure that may denote a specific response to a highpriority residual element 116. For example and without limitation,charging component 132 may experience a fire hazard in which such ahazard may result in an imminent danger, wherein residual prioritycommand 128 may be initiated. Residual priority command 128 may includean immediate shutdown and/or breaking down of all electrical circuitspowering any electrical components of system 100 and/or involved in thecharging process. Compared to a minor residual element 116, such ashutdown and/or breakdown may be executed after a delay in time as afunction of timer module 172, wherein the delay of time may provideample time to resolve residual element 116 automatically and/ormanually. This may include executing a safety lock instruction oncharging component 132. For example and without limitation, chargingcomponent 132 may detach itself from electric aircraft port 156 by anymethod of ejections on any charging connector and/or cable. In anon-limiting embodiment, charging component 132 may include clips orsprings used to hold onto a charging connector securely onto electricaircraft port 156 using clips or eject the charging connectorimmediately using springs, which may be unlocked by fastener 144.Persons skilled in the art, upon reviewing the entirety of thisdisclosure, will be aware of the various embodiments of detaching forpurposes as described herein.

With continued reference to FIG. 1 , computing device 112 may beconfigured to trip charging component 132 as a function of securitymeasure 120. In a non-limiting embodiment, computing device 112 mayoperate any switch including, but not limited to, thermal overload relay148. In a non-limiting embodiment, computing device 112 may beconfigured to perform redundancy switching as a function of thermaloverload relay 148, which may part of security measure 120. “Redundancyswitching,” for the purpose of this disclosure, is a process ofswitching a primary equipment to at least a secondary equipment inresponse to a fault, wherein the redundancy switching is configured toprotect any electrical equipment on the side of charging component 132.In a non-limiting embodiment, security measure 120 instruct computingdevice 112 to operate switch connecting battery storage unit 176 tocharging component 132 in charging an electric vehicle to a secondarybattery storage unit, wherein the secondary battery storage unit is abackup storage unit configured to maintain and power the operation ofsystem 100 in the event battery storage unit 176 is compromised due toresidual element 116. For example and without limitation, residualelement 116 may include an instance when battery storage unit 176 islacking sufficient power that is used to power not only the componentsof system 100, but also electric aircraft 152, in which computing device112 may initiate security measure 120 by operating a switch to switchfrom using the main battery storage unit 176 to the secondary storageunit. Persons skilled in the art, upon reviewing the entirety of thisdisclosure, will be aware of the various purposes for redundancyswitching as described herein.

With continued reference to FIG. 1 , computing device 112 may beconfigured to assign residual element 116 with a trip class. A “tripclass,” for the purpose of this disclosure, is a thermal current rating.For example and without limitation, a thermal class 5 is usually usedfor motors requiring fast tripping. A thermal class 10 is commonly usedto protect artificially cooled motors such as submersible pump motors oflow thermal capacity. A thermal class 20 is usually sufficient forgeneral purpose applications. Each class denotes an amount of timedelayed for a switch such as thermal overload relay 148 to trip. Forexample and without limitation, Class 10 will trip in 10 seconds orless, Class 20 will trip in 20 seconds or less, and Class 30 will tripin 30 seconds or less. In a non-limiting embodiment, security measure120 may include instructing thermal overload relay 148, as a function ofcomputing device 112, to trip charging component 132 and/or electricaircraft 152 based on a trip class. For example and without limitation,a minor residual element 116, such as a loose connection of chargingcomponent 132, an inappropriate disconnection of charging component 132,and the like thereof, may be assigned a trip class of 30. Residualelement 116 of a more severe matter which may trigger a residualpriority command such as a high voltage residual current, high voltageleakage current, an extreme electric overcharge, and the like thereof,may be assigned a trip class of 5 or less, indicating a more fastertripping process. Persons skilled in the art, upon reviewing theentirety of this disclosure, will be aware of the various shutdownprocedures for various incidents with various levels of priority andseverity for purposes as described herein.

With continued reference to FIG. 1 , security measure 120 may includeoperating a residual current device (RCD) incorporated with chargingcomponent 132. A “residual current device,” for the purpose of thisdisclosure, is a safety device configured to break any electricalcircuit to protect an electrical system and its equipment of a risk ofserious harm from an ongoing electric shock. In a non-limitingembodiment, computing device 112 may be configured to quantify residualelement 116 and then identify the source, wherein the source may includea faulty wiring, faulty battery module, faulty power source, and thelike thereof. In a non-limiting embodiment, computing device 112 may actas a voltage supervisor. Computing device 112 may monitor foralternating currents and potential residual currents using any timermodule such as a watchdog timer configured to help ensure that thecomputing device 112 does not latch by periodically detecting pulsessent by the computing device 112 general-purpose input/output pin. Ifthe software glitches and a pulse is missed, the watchdog timer willreset the computing device 112. Computing device 112 may incorporate anyRCD, for example and without limitation, the RCD may include an EarthLeakage Relay (ELR). The Earth Leakage Relay with Core Balanced Currenttransformer provides protection from earth leakage with advanceintimation (Pre-alarm) of impending occurrence of the event. As a partof security measure 120, a user can proactively take action to avoidoccurrence of any mishaps. For example and without limitation, securitymeasure 120 may have instructions to use a Rishabh's ELR with 4 digit 7segment LED display with True RMS measurement (as per IEC 60947-2 AnnexM) that provides the user with the equipment to measure low level ofleakage current and isolate the faulty equipment or circuit from thesystem. Leakage current is sensed through Rishabh's Core BalancedCurrent Transformer. Fixed time trip occurs when Earth Leakage Currentexceeds the trip time which is programmable by means of front keysprovide on the front panel of the relay or PRKAB software (can beprovided optionally with Rishabh's ELR). The user can then programresidual threshold level 164 ranging from 30 mA to 30 A. In case ofearth leakage the LED indicators will glow depending upon the percentageof programmed threshold value. For e.g. If the set level is 30 mA andthe leakage current is more than 15 mA then green LED will startblinking which will provide a visual alert to the user. This empowersthe user to take corrective actions before any accident. Core BalancedCurrent Transformer (CBCT) uses the technology of residual magneticflux. All conductors to be protected shall pass through the core balancecurrent transformer. The vector sum of all the currents should be equalto zero. Persons skilled in the art, upon reviewing the entirety of thisdisclosure, will be aware of the various embodiments and function of anyresidual current device as described herein.

With continued reference to FIG. 1 , computing device 112 may beconfigured to operate 1-phase and 3-phase inverters as a part ofsecurity measure 120. For example and without limitation, the leakagecurrents in frequency inverters arise through internalinterference-suppression measures and all parasitic capacitances in theinverter and motor cables. The largest leakage currents, though, arecaused by the method of operation of the inverter. In a non-limitingembodiment, the inverters control motor speed continuously usingpulse-width modulation (PWM), which generates leakage currents far abovethe grid frequency of 50 Hz. For instance, the switching frequency of aninverter might be 4 kHz, and the associated harmonics can have verylarge amplitudes at higher frequencies. These frequencies then travelover the motor cables to the motor, and so the motor cables with theirgrounded shields act like a capacitor to ground. Current is thendiverted to earth through this capacitance. It is thus recommended toseparate filtered and unfiltered cables, otherwise high-frequencyinterference signals can be carried over the filtered cable. Personsskilled in the art, upon reviewing the entirety of this disclosure, willbe aware of the various embodiments and functions of frequency invertersin response to residual current for purposes as described herein.

With continued reference to FIG. 1 , computing device 112 may beconfigured to operate a first mode. A “first mode,” for the purpose ofthis disclosure, is a computing device configured to execute securitymeasure 120 on electric aircraft 152. In a non-limiting embodiment,alert datum 120 denote residual element 116 identified on the side ofelectric aircraft 152. This may be detected through the connectionestablished by charging component 132. For example and withoutlimitation, the first mode may be exclusively responsible for managingand/or monitoring a security measure curated for reducing potential harmby a residual current within electric aircraft 152. In a non-limitingembodiment, the first mode is further configured may terminate one ormore connections of a battery component, such as a battery module, toits neighboring battery components, as a function of the identificationof residual element 116. In another non-limiting embodiment, computingdevice 112 may be configured to operate a second mode. A “second mode,”for the purpose of this disclosure, is a computing device configured toexecute security measure 120 on charging component 132. In anon-limiting embodiment, alert datum 120 may denote residual element 116identified on the side of charging component 132 such as its batterystorage unit 176. For example and without limitation, the second modemay trip charging component 132 in the event residual element 116 isidentified within the charging component and execute a specific securitymeasure 120 based on the trip class associated with residual element116. Persons skilled in the art, upon reviewing the entirety of thisdisclosure, will be aware of various embodiments of the first mode andsecond mode for various management purposes as described herein.

Referring now to FIG. 2 , an exemplary embodiment of a module monitorunit (MMU) 200 is presented in accordance with one or more embodimentsof the present disclosure. In one or more embodiments, MMU 200 isconfigured to monitor an operating condition of a battery pack 204. Forexample, and without limitation, MMU 200 may monitor an operatingcondition of a battery module 208 and/or a battery cell 212 of batterypack 204. Battery pack 204 may be consistent with battery pack 160 inFIG. 1 . In one or more embodiments, MMU 200 may be attached to batterymodule 208, as shown in FIG. 2 . For example, and without limitation,MMU 200 may include a housing 216 that is attached to battery module208, where circuitry of MMU 200 may be disposed at least partiallytherein, as discussed further in this disclosure. In other embodiments,MMU 200 may be remote to battery module 208. In one or more embodiments,housing 216 may include materials which possess characteristics suitablefor thermal insulation, such as fiberglass, iron fibers, polystyrenefoam, and thin plastic films, to name a few. Housing 216 may alsoinclude polyvinyl chloride (PVC), glass, asbestos, rigid laminate,varnish, resin, paper, Teflon, rubber, and mechanical lamina tophysically isolate components of battery pack 204 from externalcomponents. In one or more embodiments, housing 216 may also includelayers that separate individual components of MMU 200, which arediscussed further below in this disclosure. As understood by one skilledin the art, housing 216 may be any shape or size suitable to attached tobattery module 208 of battery pack 204.

In one or more embodiments, a plurality of MMUs 200 may be configured tomonitor battery module 208 and/or battery cell 212. For instance, andwithout limitation, a first MMU 200 a may be position at one end ofbattery module 208, and a second MMU 200 b may be positioned at anopposing end of battery module 208. This arrangement may allow forredundancy in monitoring of battery cell 212. For example, and withoutlimitation, if first MMU 200 a fails, then second MMU 200 b may continueto work properly and monitor the operating condition of each batterycell 212 of battery module 208. In one or more embodiments, MMU 200 maymonitor the operating condition of a plurality of battery cells, asshown in FIG. 2 .

In one or more embodiments, MMU 200 is configured to detect ameasurement parameter of battery module 208. For the purposes of thisdisclosure, a “measurement parameter” is detected electrical or physicalinput, characteristic, and/or phenomenon related to a state of batterypack 204. For example, and without limitation, a measurement parametermay be a temperature, a voltage, a current, a moisture level/humidity, agas level, or the like, as discussed further in this disclosure.

In one or more embodiments, MMU 200 is configured to performload-sharing during the charging of battery pack 204. For instance, MMU200 may regulate charge levels of battery cells 212. For example,charging of battery pack 204 may be shared throughout a plurality ofbattery cells 212 by directing energy through balance resistors anddissipating current through resistors as heat. For example, and withoutlimitation, resistor may include a nonlinear resistor, such as athermistor 220. In this manner, battery cells 212 may be charged evenlyduring recharging of battery pack 204 by, for example, a chargingstation or an electric grid. For example, and without limitation,battery cells with a lower amount of electrical energy will charge morethan battery cells with a greater amount of energy.

In one or more embodiments, MMU 200 is configured to monitor atemperature of battery module 208. For example, MMU 200 may include asensor 224 configured to detect a temperature parameter of battery cell212. For example, and without limitation, sensor 224 may includethermistor 220, which may be used to measure a temperature parameter ofbattery cell 212. As used in this disclosure, a thermistor includes aresistor having a resistance dependent on temperature. In one or moreembodiments, sensor 224 may include circuitry configured to generate ameasurement datum correlated to the detected measurement parameter, suchas a temperature of battery cell 212 detected by thermistor 220. Athermistor may include metallic oxides, epoxy, glass, and the like. Athermistor may include a negative temperature coefficient (NTC) or apositive temperature coefficient (PTC). Thermistors may be beneficial doto being durable, compact, inexpensive, and relatively accurate. In oneor more embodiments, a plurality of thermistors 220 may be used toprovide redundant measuring of a state of battery cell 212, such astemperature. In other embodiments, MMU 200 may also include a resistancetemperature detector (RTD), integrated circuit, thermocouple,thermometer, microbolometer, a thermopile infrared sensor, and/or othertemperature and/or thermal sensors, as discussed further below in thisdisclosure. In one or more embodiments, thermistor 220 may detect atemperature of battery cell 212. Subsequently, MMU 200 may generate asensor signal output containing information related to the detectedtemperature of battery cell 212. In one or more embodiments, sensorsignal output may include measurement datum containing informationrepresenting a detected measurement parameter.

In one or more embodiments, sensor 224 may include a sensor suite 200(shown in FIG. 2 ) or one or more individual sensors, which may include,but are not limited to, one or more temperature sensors, voltmeters,current sensors, hydrometers, infrared sensors, photoelectric sensors,ionization smoke sensors, motion sensors, pressure sensors, radiationsensors, level sensors, imaging devices, moisture sensors, gas andchemical sensors, flame sensors, electrical sensors, imaging sensors,force sensors, Hall sensors, airspeed sensors, throttle positionsensors, and the like. Sensor 224 may be a contact or a non-contactsensor. For example, and without limitation, sensor 224 may be connectedto battery module 208 and/or battery cell 212. In other embodiments,sensor 224 may be remote to battery module and/or battery cell 212.Sensor 224 may be communicatively connected to controller 320 of PMU 312(shown in FIG. 3 ) so that sensor 224 may transmit/receive signalsto/from controller 320, respectively, as discussed below in thisdisclosure. Signals, such as signals of sensor 224 and controller 320,may include electrical, electromagnetic, visual, audio, radio waves, oranother undisclosed signal type alone or in combination. In one or moreembodiments, communicatively connecting is a process whereby one device,component, or circuit is able to receive data from and/or transmit datato another device, component, or circuit. In an embodiment,communicative connecting includes electrically connecting at least anoutput of one device, component, or circuit to at least an input ofanother device, component, or circuit.

In one or more embodiments, MMU 200 may include a control circuit thatprocesses the received measurement datum from sensor 224, as shown inFIG. 3 . In one or more embodiments, control circuit may be configuredto perform and/or direct any actions performed by MMU 200 and/or anyother component and/or element described in this disclosure. Controlcircuit may include any analog or digital control circuit, includingwithout limitation a combinational and/or synchronous logic circuit, aprocessor, microprocessor, microcontroller, any combination thereof, orthe like. In some embodiments, control circuit 228 may be integratedinto MMU 200, as shown in FIG. 2 . In other embodiments, control circuit228 may be remote to MMU 200. In one or more nonlimiting exemplaryembodiments, if measurement datum of a temperature of a battery module208, such as at a terminal 232, is higher than a predeterminedthreshold, control circuit 228 may determine that the temperature ofbattery cell 212 indicates a critical event and thus is malfunctioning.For example, a high voltage (HV) electrical connection of battery moduleterminal 232 may be short circuiting. If control circuit 228 determinesthat a HV electrical connection is malfunctioning, control circuit 228may terminate a physical and/or electrical communication of the HVelectrical connection to prevent a dangerous or detrimental reaction,such as a short, that may result in an electrical shock, damage tobattery pack 204, or even a fire. Thus, control circuit 228 may trip acircuit of battery pack 204 and terminate power flow through the faultybattery module 208 until the detected fault is corrected and/or theexcessively high temperature is no longer detected. Temperature sensors,such as thermistor 220 may assist in the monitoring of a cell group'soverall temperature, an individual battery cell's temperature, and/orbattery module's temperature, as just described above.

In one or more embodiments, MMU 200 may not use software. For example,MMU 200 may not use software to improve reliability and durability ofMMU 200. Rather, MMU 200 may be communicatively connected to a remotecomputing device, such as computing device 800 of FIG. 8 . In one ormore embodiments, MMU 200 may include one or more circuits and/orcircuit elements, including without limitation a printed circuit boardcomponent, aligned with a first side of battery module 208 and theopenings correlating to battery cells 212. In one or more embodiments,MMU 200 may be communicatively connected to a remote processing module,such as a controller. Controller may be configured to performappropriate processing of detected temperature characteristics by sensor224. In one or more embodiments, controller ** may include anapplication-specific integrated circuit (ASIC), field-programmable gatearray (FPGA), a central processing unit (CPU), readout integratedcircuit (ROIC), or the like, and may be configured to performcharacteristic processing to determine a temperature and/or criticalevent of battery module 208. In these and other embodiments, controllermay operate in conjunction with other components, such as, a memorycomponent, where a memory component includes a volatile memory and/or anon-volatile memory.

In one or more embodiments, each MMU 200 may communicate with anotherMMU 200 and/or a controller via a communicative connection 236. Each MMUmay use a wireless and/or wired connection to communicated with eachother. For example, and without limitation, MMU 200 a may communicatewith an adjacent MMU 200 a using an isoSPI connection 304 (shown in FIG.3 ). As understood by one skilled in the art, and isoSPI connection mayinclude a transformer to magnetically connect and electrically isolate asignal between communicating devices.

Now referring to FIG. 3 , a battery pack 160 with a battery managementcomponent 300 that utilizes MMU 200 for monitoring a status of batterypack is shown in accordance with one or more embodiments of the presentdisclosure. In one or more embodiments, electric aircraft battery pack160 may include a battery module 208, which is configured to provideenergy to an electric aircraft 304 via a power supply connection 308.For the purposes of this disclosure, a “power supply connection” is anelectrical and/or physical communication between a battery module 208and electric aircraft 304 that powers electric aircraft 304 and/orelectric aircraft subsystems for operation. In one or more embodiments,battery pack 160 may include a plurality of battery modules, such asmodules 208 a-n. For example, and without limitation, battery pack 160may include fourteen battery modules. In one or more embodiments, eachbattery module 208 a-n may include a battery cell 212 (shown in FIG. 2).

Still referring to FIG. 3 , battery pack 160 may include a batterymanagement component 220 (also referred to herein as a “managementcomponent”). In one or more embodiments, battery management component300 may be integrated into battery pack 160 in a portion of battery pack160 or a subassembly thereof. In an exemplary embodiment, and withoutlimitation, management component 300 may be disposed on a first end ofbattery pack 160. One of ordinary skill in the art will appreciate thatthere are various areas in and on a battery pack and/or subassembliesthereof that may include battery management component 300. In one ormore embodiments, battery management component 300 may be disposeddirectly over, adjacent to, facing, and/or near a battery module andspecifically at least a portion of a battery cell. In one or moreembodiments, battery management component 300 includes module monitorunit (MMU) 200, a pack monitoring unit (PMU) 312, and a high voltagedisconnect 316. In one or more embodiments, battery management component300 may also include a sensor 224. For example, and without limitation,battery management component 300 may include a sensor suite 200 having aplurality of sensors, as discussed further in this disclosure, as shownin FIG. 2 .

In one or more embodiments, MMU 200 may be mechanically connected andcommunicatively connected to battery module 208. As used herein,“communicatively connected” is a process whereby one device, component,or circuit is able to receive data from and/or transmit data to anotherdevice, component, or circuit. In an embodiment, communicativeconnecting includes electrically connecting at least an output of onedevice, component, or circuit to at least an input of another device,component, or circuit. In one or more embodiments, MMU 200 is configuredto detect a measurement characteristic of battery module 208 of batterypack 160. For the purposes of this disclosure, a “measurementcharacteristic” is detected electrical or physical input and/orphenomenon related to a condition state of battery pack 160. A conditionstate may include detectable information related to, for example, atemperature, a moisture level, a humidity, a voltage, a current, ventgas, vibrations, chemical content, or other measurable characteristicsof battery pack 160, battery module 208, and/or battery cell 212. Forexample, and without limitation, MMU 200 may detect and/or measure ameasurement characteristic, such as a temperature, of battery module208. In one or more embodiments, a condition state of battery pack 160may include a condition state of a battery module 208 and/or batterycell 212. In one or more embodiments, MMU 200 may include a sensor,which may be configured to detect and/or measure measurementcharacteristic. As used in this disclosure, a “sensor” is a device thatis configured to detect an input and/or a phenomenon and transmitinformation and/or datum related to the detection, as discussed furtherbelow in this disclosure. Output signal may include a sensor signal,which transmits information and/or datum related to the sensordetection. A sensor signal may include any signal form described in thisdisclosure, for example digital, analog, optical, electrical, fluidic,and the like. In some cases, a sensor, a circuit, and/or a controllermay perform one or more signal processing steps on a signal. Forinstance, sensor, circuit, and/or controller may analyze, modify, and/orsynthesize a signal in order to improve the signal, for instance byimproving transmission, storage efficiency, or signal to noise ratio.

In one or more embodiments, MMU 200 is configured to transmit ameasurement datum of battery module 208. MMU 200 may generate an outputsignal such as measurement datum that includes information regardingdetected measurement characteristic. For the purposes of thisdisclosure, “measurement datum” is an electronic signal representing aninformation and/or a parameter of a detected electrical and/or physicalcharacteristic and/or phenomenon correlated with a condition state ofbattery pack 160. For example, measurement datum may include data of ameasurement characteristic regarding a detected temperature of batterycell 212. In one or more embodiments, measurement datum may betransmitted by MMU 200 to PMU 312 so that PMU 312 may receivemeasurement datum, as discussed further in this disclosure. For example,MMU 200 may transmit measurement data to a controller 320 of PMU 312.

In one or more embodiments, MMU 200 may include a plurality of MMUs. Forinstance, and without limitation, each battery module 208 a-n mayinclude one or more MMUs 200. For example, and without limitation, eachbattery module 208 a-n may include two MMUs 200 a,b. MMUs 200 a,b may bepositioned on opposing sides of battery module 208. Battery module 208may include a plurality of MMUs to create redundancy so that, if one MMUfails or malfunctions, another MMU may still operate properly. In one ormore nonlimiting exemplary embodiments, MMU 200 may include maturetechnology so that there is a low risk. Furthermore, MMU 200 may notinclude software, for example, to avoid complications often associatedwith programming. MMU 200 is configured to monitor and balance allbattery cell groups of battery pack 160 during charging of battery pack160. For instance, and without limitation, MMU 200 may monitor atemperature of battery module 208 and/or a battery cell of batterymodule 208. For example, and without limitation, MMU may monitor abattery cell group temperature. In another example, and withoutlimitation, MMU 200 may monitor a terminal temperature to, for example,detect a poor HV electrical connection. In one or more embodiments, anMMU 200 may be indirectly connected to PMU 312. In other embodiments,MMU 200 may be directly connected to PMU 312. In one or moreembodiments, MMU 200 may be communicatively connected to an adjacent MMU200.

Still referring to FIG. 3 , battery management component 300 includes apack monitoring unit (PMU) 228 may be connected to MMU 200. In one ormore embodiments, PMU 312 includes a controller 320, which is configuredto receive measurement datum from MMU 200, as previously discussed inthis disclosure. For example, PMU 312 a may receive a plurality ofmeasurement data from MMU 200 a. Similarly, PMU 312 b may receive aplurality of measurement data from MMU 200 b. In one or moreembodiments, PMU 312 may receive measurement datum from MMU 200 viacommunicative connections. For example, PMU 312 may receive measurementdatum from MMU 200 via an isoSPI communications interface. In one ormore embodiments, controller 320 of PMU 312 is configured to identify anoperating of battery module 208 as a function of measurement datum. Forthe purposes of this disclosure, an “operating condition” is a stateand/or working order of battery pack 160 and/or any components thereof.For example, and without limitation, an operating condition may includea state of charge (SoC), a depth of discharge (DoD), a temperaturereading, a moisture level or humidity, a gas level, a chemical level, orthe like. In one or more embodiments, controller 320 of PMU 312 isconfigured to determine a critical event element if operating conditionis outside of a predetermined threshold (also referred to herein as a“predetermined threshold”). For the purposes of this disclosure, a“critical event element” is a failure and/or critical operatingcondition of a battery pack, battery cell, and/or battery module thatmay be harmful to battery pack 160 and/or electric aircraft 304. Forinstance, and without limitation, if an identified operating condition,such as a temperature of a battery cell 212 of battery pack 160, doesnot fall within a predetermined threshold, such as a range ofacceptable, operational temperatures of the battery cell, then acritical event element is determined by controller 320 of PMU 312. Forexample, and without limitation, PMU may be used measurement datum fromMMU to identify a temperature of 95 degrees Fahrenheit for a batterycell. If the predetermined threshold is, for example, 75 to 90 degreesFahrenheit, then the determined operating condition is outside of thepredetermined threshold, such as exceeding the upper limit of 90 degreesFahrenheit, and a critical event element is determined by controller320. As used in this disclosure, a “predetermined threshold” is a limitand/or range of an acceptable quantitative value and/or representationrelated to a normal operating condition of a battery pack and/orcomponents thereof. In one or more embodiments, an operating conditionoutside of the threshold is a critical operating condition, whichtriggers a critical event element, and an operating condition within thethreshold is a normal operating condition that indicates that batterypack 160 is working properly. For example, and without limitation, if anoperating condition of temperature exceeds a predetermined threshold,then battery pack is considered to be operating at a critical operatingcondition and may be at risk of overheating and experiencing acatastrophic failure.

In one or more embodiments, controller 320 of PMU 312 is configured togenerate an action command if critical event element is determined bycontroller 320. Continuing the previously described example above, if anidentified operating condition includes a temperature of 95 degreesFahrenheit, which exceeds a predetermined threshold, then controller 320may determine a critical event element indicating that battery pack 160is working at a critical temperature level and at risk of catastrophicfailure. In one or more embodiments, critical event elements may includehigh shock/drop, overtemperature, undervoltage, high moisture, contactorwelding, and the like.

In one or more embodiments, controller 320 may include a computingdevice (as discussed in FIG. 8 ), a central processing unit (CPU), amicroprocessor, a digital signal processor (DSP), an applicationspecific integrated circuit (ASIC), a control circuit, a combinationthereof, or the like. In one or more embodiments, output signals fromvarious components of battery pack 160 may be analog or digital.Controller 320 may convert output signals from MMU 200 and/or sensor 224to a usable form by the destination of those signals. The usable form ofoutput signals from MMUs and/or sensors, through processor may be eitherdigital, analog, a combination thereof, or an otherwise unstated form.Processing may be configured to trim, offset, or otherwise compensatethe outputs of sensor. Based on MMU and/or sensor output, controller candetermine the output to send to a downstream component. Processor caninclude signal amplification, operational amplifier (Op-Amp), filter,digital/analog conversion, linearization circuit, current-voltage changecircuits, resistance change circuits such as Wheatstone Bridge, an errorcompensator circuit, a combination thereof or otherwise undisclosedcomponents. In one or more embodiments, PMU 312 may run state estimationalgorithms.

In one or more embodiments, MMU 200 may be implemented in batterymanagement system 300 of battery pack 160. MMU 200 may include sensor224, as previously mentioned above in this disclosure. For instance, andwithout limitation, MMU 200 may include a plurality of sensors. Forexample, MMU 200 may include thermistors 220 to detect a temperature ofa corresponding battery module 208 and/or battery cell 212. MMU 200 mayinclude sensor 220 or a sensor suite, such as sensor suite 200 of FIG. 2, that is configured to measure physical and/or electrical parameters ofbattery pack 160, such as without limitation temperature, voltage,current, orientation, or the like, of one or more battery modules and/orbattery cells 212. MMU 200 may configured to generate a measurementdatum of each battery cell 212, which a control circuit may ultimatelyuse to determine a failure within battery module 208 and/or battery cell212, such as a critical event element. Cell failure may be characterizedby a spike in temperature and MMU 200 may be configured to detect thatincrease, which in turn, PMU 312 uses to determine a critical eventelement and generate signals, to disconnect a power supply connectionbetween electric aircraft ** and battery cell 212 and to notify users,support personnel, safety personnel, maintainers, operators, emergencypersonnel, aircraft computers, or a combination thereof. In one or moreembodiments, measurement data of MMU may be stored in memory component324.

Still referring to FIG. 3 , battery management component 300 may includehigh voltage disconnect 232, which is communicatively connected tobattery module 208, wherein high voltage disconnect 232 is configured toterminate power supply connection 212 between battery module 208 andelectric aircraft 304 in response to receiving action command from PMU312. PMU 312 may be configured to determine a critical event element,such as high shock/drop, overtemperature, undervoltage, contactorwelding, and the like. High voltage disconnect 232 is configured toreceive action command generated by PMU 312 and lock out battery pack160 for maintenance in response to received action command. In one ormore embodiments, PMU 312 may create a lockout flag, which may be savedacross reboots. A lockout flag may include an indicator alerting a userof termination of power supply connection 212 by high voltage disconnect232. For instance, and without limitation, a lockout flag may be savedin a database od PMU 312 so that, despite rebooting battery pack 160 orcomplete loss of power of battery pack 160, power supply connectionremains terminated and an alert regarding the termination remains. Inone or more embodiments, lockout flag cannot be removed until a criticalevent element is no longer determined by controller 320. For, example,PMU 312 may be continuously updating an operating condition anddetermining if operating condition is outside of a predeterminedthreshold. In one or more embodiments, lockout flag may include an alerton a graphic user interface of, for example, a remote computing device,such as a mobile device, tablet, laptop, desktop and the like. In otherembodiments, lockout flag may be indicated to a user via an illuminatedLED that is remote or locally located on battery pack 160. In one ormore embodiments, PMU 312 may include control of cell group balancingvia MMUs, control of contactors (high voltage connections, etc.) controlof welding detection, control of pyro fuses, and the like.

In one or more embodiments, battery management component 300 may includea plurality of PMUs 312. For instance, and without limitation, batterymanagement component 300 may include a pair of PMUs. For example, andwithout limitation, battery management component 300 may include a firstPMU 312 a and a second PMU 312 b, which are each disposed in or onbattery pack 160 and may be physically isolated from each other.“Physical isolation”, for the purposes of this disclosure, refer to afirst system's components, communicative connection, and any otherconstituent parts, whether software or hardware, are separated from asecond system's components, communicative coupling, and any otherconstituent parts, whether software or hardware, respectively.Continuing in reference to the nonlimiting exemplary embodiment, firstPMU 312 a and second PMU 312 b may perform the same or differentfunctions. For example, and without limitation, the first and secondPMUs 312 a,b may perform the same, and therefore, redundant functions.Thus, if one PMU 312 a/b fails or malfunctions, in whole or in part, theother PMU 312 b/a may still be operating properly and therefore batterymanagement component 300 may still operate and function properly forbattery pack 160. One of ordinary skill in the art would understand thatthe terms “first” and “second” do not refer to either PMU as primary orsecondary. In non-limiting embodiments, the first and second PMUs 312a,b, due to their physical isolation, may be configured to withstandmalfunctions or failures in the other system and survive and operate.Provisions may be made to shield first PMU 312 a from PMU 312 b otherthan physical location, such as structures and circuit fuses. Innon-limiting embodiments, first PMU 312 a, second PMU 312 b, orsubcomponents thereof may be disposed on an internal component or set ofcomponents within battery pack 160, such as on battery module senseboard, as discussed further below in this disclosure.

Still referring to FIG. 3 , first PMU 312 a may be electrically isolatedfrom second PMU 312 b. “Electrical isolation”, for the purposes of thisdisclosure, refer to a first system's separation of components carryingelectrical signals or electrical energy from a second system'scomponents. First PMU 312 a may suffer an electrical catastrophe,rendering it inoperable, and due to electrical isolation, second PMU 312b may still continue to operate and function normally, allowing forcontinued management of battery pack 160 of electric aircraft 304.Shielding such as structural components, material selection, acombination thereof, or another undisclosed method of electricalisolation and insulation may be used, in nonlimiting embodiments. Forexample, and without limitation, a rubber or other electricallyinsulating material component may be disposed between electricalcomponents of first and second PMUs 312 a,b, preventing electricalenergy to be conducted through it, isolating the first and second PMUs312 a,b form each other.

With continued reference to FIG. 3 , battery management component 300may include memory component 324, as previously mentioned above in thisdisclosure. In one or more embodiments, memory component 324 may beconfigured to store datum related to battery pack 160, such as datarelated to battery modules 208 a-n and/or battery cells 212. Forexample, and without limitation, memory component 324 may store sensordatum, measurement datum, operation condition, critical event element,lockout flag, and the like. Memory component 324 may include a database.Memory component 324 may include a solid-state memory or tape harddrive. Memory component 324 may be communicatively connected to PMU 312and may be configured to receive electrical signals related to physicalor electrical phenomenon measured and store those electrical signals asbattery module data. Alternatively, memory component 324 may be aplurality of discrete memory components that are physically andelectrically isolated from each other. One of ordinary skill in the artwould understand the virtually limitless arrangements of data storeswith which battery pack 160 could employ to store battery pack data.

Referring now to FIG. 4 , an embodiment of battery management system 400is presented. Battery management system 400 is be integrated in abattery pack 160 configured for use in an electric aircraft. The batterymanagement system 400 is be integrated in a portion of the battery pack160 or subassembly thereof. Battery management system 400 includes firstbattery management component 408 disposed on a first end of the batterypack. One of ordinary skill in the art will appreciate that there arevarious areas in and on a battery pack and/or subassemblies thereof thatmay include first battery management component 408. First batterymanagement component 408 may take any suitable form. In a non-limitingembodiment, first battery management component 408 may include a circuitboard, such as a printed circuit board and/or integrated circuit board,a subassembly mechanically coupled to at least a portion of the batterypack, standalone components communicatively coupled together, or anotherundisclosed arrangement of components; for instance, and withoutlimitation, a number of components of first battery management component408 may be soldered or otherwise electrically connected to a circuitboard. First battery management component may be disposed directly over,adjacent to, facing, and/or near a battery module and specifically atleast a portion of a battery cell. First battery management component408 includes first sensor suite 412. First sensor suite 412 isconfigured to measure, detect, sense, and transmit first plurality ofbattery pack datum 424 to battery database 404.

Referring again to FIG. 4 , battery management system 400 includessecond battery management component 416. For instance and withoutlimitation, battery management system may be consistent with disclosureof battery management system in U.S. patent application Ser. No.17/108,798 and titled “SYSTEMS AND METHODS FOR A BATTERY MANAGEMENTSYSTEM INTEGRATED IN A BATTERY PACK CONFIGURED FOR USE IN ELECTRICAIRCRAFT,” which is incorporated herein by reference in its entirety.Second battery management component 416 is disposed in or on a secondend of battery pack 160. Second battery management component 416includes second sensor suite 420. Second sensor suite 420 may beconsistent with the description of any sensor suite disclosed herein.Second sensor suite 420 is configured to measure second plurality ofbattery pack datum 428. Second plurality of battery pack datum 428 maybe consistent with the description of any battery pack datum disclosedherein. Second plurality of battery pack datum 428 may additionally oralternatively include data not measured or recorded in another sectionof battery management system 400. Second plurality of battery pack datum428 may be communicated to additional or alternate systems to which itis communicatively coupled. Second sensor suite 420 includes a moisturesensor consistent with any moisture sensor disclosed herein, namelymoisture sensor 408.

With continued reference to FIG. 4 , first battery management component408 disposed in or on battery pack 160 may be physically isolated fromsecond battery management component 416 also disposed on or in batterypack 160. “Physical isolation”, for the purposes of this disclosure,refer to a first system's components, communicative coupling, and anyother constituent parts, whether software or hardware, are separatedfrom a second system's components, communicative coupling, and any otherconstituent parts, whether software or hardware, respectively. In anon-limiting embodiment, the plurality of the first and second batterymanagement component may be outside the battery pack 160. First batterymanagement component 408 and second battery management component 416 mayperform the same or different functions in battery management system400. In a non-limiting embodiment, the first and second batterymanagement components perform the same, and therefore redundantfunctions. If, for example, first battery management component 408malfunctions, in whole or in part, second battery management component416 may still be operating properly and therefore battery managementsystem 400 may still operate and function properly for electric aircraftin which it is installed. Additionally or alternatively, second batterymanagement component 416 may power on while first battery managementcomponent 408 is malfunctioning. One of ordinary skill in the art wouldunderstand that the terms “first” and “second” do not refer to either“battery management components” as primary or secondary. In non-limitingembodiments, first battery management component 408 and second batterymanagement component 416 may be powered on and operate through the sameground operations of an electric aircraft and through the same flightenvelope of an electric aircraft. This does not preclude one batterymanagement component, first battery management component 408, fromtaking over for second battery management component 416 if it were tomalfunction. In non-limiting embodiments, the first and second batterymanagement components, due to their physical isolation, may beconfigured to withstand malfunctions or failures in the other system andsurvive and operate. Provisions may be made to shield first batterymanagement component 408 from second battery management component 416other than physical location such as structures and circuit fuses. Innon-limiting embodiments, first battery management component 408, secondbattery management component 416, or subcomponents thereof may bedisposed on an internal component or set of components within batterypack 160, such as on battery module sense board 404.

Referring again to FIG. 4 , first battery management component 408 maybe electrically isolated from second battery management component 416.“Electrical isolation”, for the purposes of this disclosure, refer to afirst system's separation of components carrying electrical signals orelectrical energy from a second system's components. First batterymanagement component 408 may suffer an electrical catastrophe, renderingit inoperable, and due to electrical isolation, second batterymanagement component 416 may still continue to operate and functionnormally, managing the battery pack of an electric aircraft. Shieldingsuch as structural components, material selection, a combinationthereof, or another undisclosed method of electrical isolation andinsulation may be used, in non-limiting embodiments. For example, arubber or other electrically insulating material component may bedisposed between the electrical components of the first and secondbattery management components preventing electrical energy to beconducted through it, isolating the first and second battery managementcomponents from each other.

With continued reference to FIG. 4 , battery management system 400includes battery database 404. Battery database 404 is configured tostore first plurality of battery pack datum 424 and second plurality ofbattery pack datum 428. Battery database 404 may include a database.Battery database 404 may include a solid-state memory or tape harddrive. Battery database 404 may be communicatively coupled to firstbattery management component 408 and second battery management component416 and may be configured to receive electrical signals related tophysical or electrical phenomenon measured and store those electricalsignals as first battery pack datum 424 and second battery pack datum428, respectively. Alternatively, battery database 404 may include morethan one discrete battery databases that are physically and electricallyisolated from each other. In this non-limiting embodiment, each of firstbattery management component 408 and second battery management component416 may store first battery pack datum 424 and second battery pack datum428 separately. One of ordinary skill in the art would understand thevirtually limitless arrangements of data stores with which batterymanagement system 400 could employ to store the first and secondplurality of battery pack datum.

Referring again to FIG. 4 , battery database 404 stores first pluralityof battery pack datum 424 and second plurality of battery pack datum428. First plurality of battery pack datum 424 and second plurality ofbattery pack datum 428 may include total flight hours that battery pack160 and/or electric aircraft have been operating. The first and secondplurality of battery pack datum may include total energy flowed throughbattery pack 160. Battery database 404 may be implemented, withoutlimitation, as a relational database, a key-value retrieval datastoresuch as a NOSQL database, or any other format or structure for use as adatastore that a person skilled in the art would recognize as suitableupon review of the entirety of this disclosure. Battery database 404 maycontain datasets that may be utilized by an unsupervisedmachine-learning model to find trends, cohorts, and shared datasetsbetween data contained within battery database 404 and first batterypack datum 424 and/or second battery pack datum 428. In an embodiment,datasets contained within battery database 404 may be categorized and/ororganized according to shared characteristics. For instance and withoutlimitation, one or more tables contained within battery database 404 mayinclude first battery pack datum table. First battery pack datum tablemay contain datasets classified to first battery pack information offirst battery pack datum. First battery pack information may includedatasets describing any first battery pack datum as described herein.One or more tables contained within battery database 404 may include asecond battery pack datum table. second battery pack datum table maycontain datasets classified to second battery pack information of secondbattery pack datum. Second battery pack information may include datasetsdescribing any second battery pack datum as described herein. One ormore tables contained within battery database 404 may include acomparison datum table. Comparison datum table may include datasetsclassified by level of comparison between first battery pack datum 424and second battery pack datum 428. Comparison datum table may includedatasets classified by the severity of the difference of the comparisonof the first and second battery pack datum from the differentialthreshold. Battery database 404 may be communicatively coupled tosensors that detect, measure and store energy in a plurality ofmeasurements which may include current, voltage, resistance, impedance,coulombs, watts, temperature, or a combination thereof. Additionally oralternatively, battery database 404 may be communicatively coupled to asensor suite consistent with this disclosure to measure physical and/orelectrical characteristics. Battery database 404 may be configured tostore first battery pack datum 424 and second battery pack datum 428wherein at least a portion of the data includes battery pack maintenancehistory. Battery pack maintenance history may include mechanicalfailures and technician resolutions thereof, electrical failures andtechnician resolutions thereof. Additionally, battery pack maintenancehistory may include component failures such that the overall systemstill functions. Battery database 404 may store the first and secondbattery pack datum that includes an upper voltage threshold and lowervoltage threshold consistent with this disclosure. First battery packdatum 424 and second battery pack datum 428 may include a moisture levelthreshold. The moisture level threshold may include an absolute,relative, and/or specific moisture level threshold. Battery managementsystem 400 may be designed to the Federal Aviation Administration(FAA)'s Design Assurance Level A (DAL-A), using redundant DAL-Bsubsystems.

With continued reference to FIG. 4 , battery management system 400 mayinclude a data collection system, which may include a central sensorsuite which may be used for first sensor suite 412 in first batterymanagement component 160 or second sensor suite 420 in second batterymanagement component 212 or consistent with any sensor suite disclosedhereinabove. Data collection system includes battery database 404.Central sensor suite is configured to measure physical and/or electricalphenomena and characteristics of battery pack 160, in whole or in part.Central sensor suite then transmits electrical signals to batterydatabase 404 to be saved. Those electrical signals are representative offirst battery pack datum 424 and second battery pack datum 428. Theelectrical signals communicated from central sensor suite, and moremoreover from the first or second battery management component 416 towhich it belongs may be transformed or conditioned consistent with anysignal conditioning present in this disclosure. Data collection systemand more specifically first battery management component 160, may beconfigured to save first battery pack datum 424 and second battery packdatum 428 periodically in regular intervals to battery database 404.“Regular intervals”, for the purposes of this disclosure, refers to anevent taking place repeatedly after a certain amount of elapsed time.Data collection system may include first battery management component160, which may include timer 504. Timer 504 may include a timingcircuit, internal clock, or other circuit, component, or part configuredto keep track of elapsed time and/or time of day. For example, innon-limiting embodiments, battery database 404 may save the first andsecond battery pack datum every 30 seconds, every minute, every 30minutes, or another time period according to timer module 172.Additionally or alternatively, battery database 404 may save the firstand second battery pack datum after certain events occur, for example,in non-limiting embodiments, each power cycle, landing of the electricaircraft, when battery pack is charging or discharging, or scheduledmaintenance periods. In non-limiting embodiments, battery pack 160phenomena may be continuously measured and stored at an intermediarystorage location, and then permanently saved by battery database 404 ata later time, like at a regular interval or after an event has takenplace as disclosed hereinabove. Additionally or alternatively, batterydatabase may be configured to save first battery pack datum 424 andsecond battery pack datum 428 at a predetermined time. “Predeterminedtime”, for the purposes of this disclosure, refers to an internal clockwithin battery management system 400 commanding battery database 404 tosave the first and second battery pack datum at that time. For example,battery database 404 may be configured to save the first and secondbattery pack datum at 0600 hours, 11 P.M. EDT, another time, multipletimes a day, and/or the like.

Now referring to FIG. 5 , an exemplary embodiment of fuzzy setcomparison 500 for a threshold is illustrated. A first fuzzy set 504 maybe represented, without limitation, according to a first membershipfunction 508 representing a probability that an input falling on a firstrange of values 512 is a member of the first fuzzy set 504, where thefirst membership function 508 has values on a range of probabilitiessuch as without limitation the interval [0,1], and an area beneath thefirst membership function 508 may represent a set of values within firstfuzzy set 504. Although first range of values 512 is illustrated forclarity in this exemplary depiction as a range on a single number lineor axis, first range of values 512 may be defined on two or moredimensions, representing, for instance, a Cartesian product between aplurality of ranges, curves, axes, spaces, dimensions, or the like.First membership function 508 may include any suitable function mappingfirst range 512 to a probability interval, including without limitationa triangular function defined by two linear elements such as linesegments or planes that intersect at or below the top of the probabilityinterval. As a non-limiting example, triangular membership function maybe defined as:

${y\left( {x,a,b,c} \right)} = \left\{ \begin{matrix}{0,{{{for}x} > {c{and}x} < a}} \\{\frac{x - a}{b - a},{{{for}a} \leq x < b}} \\{\frac{c - x}{c - b},{{{if}b} < x \leq c}}\end{matrix} \right.$a trapezoidal membership function may be defined as:

${y\left( {x,a,b,c,d} \right)} = {\max\left( {{\min\left( {\frac{x - a}{b - a},1,\frac{d - x}{d - c}} \right)},0} \right)}$a sigmoidal function may be defined as:

${y\left( {x,a,c} \right)} = \frac{1}{1 - e^{- {a({x - c})}}}$a Gaussian membership function may be defined as:

${y\left( {x,c,\sigma} \right)} = e^{{- \frac{1}{2}}{(\frac{x - c}{\sigma})}^{2}}$and a bell membership function may be defined as:

${y\left( {x,a,b,c,} \right)} = \left\lbrack {1 + {❘\frac{x - c}{a}❘}^{2b}} \right\rbrack^{- 1}$Persons skilled in the art, upon reviewing the entirety of thisdisclosure, will be aware of various alternative or additionalmembership functions that may be used consistently with this disclosure.

With continued reference to FIG. 5 , first fuzzy set 504 may representany value or combination of values as described above, including anyfault element 116 such as, but not limited to, rate of charge, rate ofdischarge, state of health, and the like thereof. A second fuzzy set516, which may represent any value which may be represented by firstfuzzy set 504, may be defined by a second membership function 520 on asecond range 524; second range 524 may be identical and/or overlap withfirst range 512 and/or may be combined with first range via Cartesianproduct or the like to generate a mapping permitting evaluation overlapof first fuzzy set 504 and second fuzzy set 516. Where first fuzzy set504 and second fuzzy set 516 have a region 228 that overlaps, firstmembership function 508 and second membership function 520 may intersectat a point 532 representing a probability, as defined on probabilityinterval, of a match between first fuzzy set 504 and second fuzzy set516. Alternatively or additionally, a single value of first and/orsecond fuzzy set may be located at a locus 536 on first range 512 and/orsecond range 524, where a probability of membership may be taken byevaluation of first membership function 508 and/or second membershipfunction 520 at that range point. A probability at 528 and/or 532 may becompared to a threshold 540 to determine whether a positive match isindicated. Threshold 540 may, in a non-limiting example, represent adegree of match between first fuzzy set 504 and second fuzzy set 516,and/or single values therein with each other or with either set, whichis sufficient for purposes of the matching process. For example andwithout limitation, the threshold may indicate a sufficient degree ofoverlap between residual element 116 and a value representing apotential residual element that may indicate a sufficient match forpurposes of generating alert datum 124 and/or determining whetherresidual element 116 indicates a threat of a danger posed by a residualcurrent. For example and without limitation, sensor 104 may detect anabnormally a high current flow from charging component 132, which may beindicative of a leakage current. Computing device 112 may denote thisevent as a means to generate alert datum 124. Each threshold may beestablished by one or more user inputs. Alternatively or additionally,each threshold may be tuned by a machine-learning and/or statisticalprocess, for instance and without limitation as described in furtherdetail below.

With continued reference to FIG. 5 , in an embodiment, a degree of matchbetween fuzzy sets may be used to rank one resource against another. Forinstance, if two predictive prevalence values have fuzzy sets matching aprobabilistic outcome fuzzy set by having a degree of overlap exceedinga threshold, computing device 104 may further rank the two resources byranking a resource having a higher degree of match more highly than aresource having a lower degree of match. Where multiple fuzzy matchesare performed, degrees of match for each respective fuzzy set may becomputed and aggregated through, for instance, addition, averaging, orthe like, to determine an overall degree of match, which may be used torank resources; selection between two or more matching resources may beperformed by selection of a highest-ranking resource, and/or multipleresidual element 116 and/or alert datum 124 may be presented to a userin order of ranking for purposes of generating and executing securityprotocol 120.

Now referring to FIG. 6 , a flow diagram of an exemplary method 600 formanaging residual energy for an electric aircraft is provided. Method600, at step 605, may include generating, by at least a pack monitorunit, a battery pack datum from a battery pack of an electric aircraft.The at least a pack monitor unit may include any pack monitor unit asdescribed herein. The battery pack datum may include any battery packdatum as described herein. The battery pack may include any battery packas described herein. The electric aircraft may include any electricaircraft as described herein. Persons skilled in the art, upon reviewingthe entirety of this disclosure, will be aware of the various methods ofdetecting data from a battery of an electric aircraft and generating acollection of information for purposes as described herein.

With continued reference to FIG. 6 , method 600, at step 610, mayinclude detecting, by a sensor communicatively connected to a chargingcomponent, a at least an electrical parameter as a function of thecharging component and the electric aircraft. The sensor may include anysensor as described herein. The charging component may include anycharging component as described herein. The plurality of measure chargedata may include any plurality of measure charge data as describedherein. In a non-limiting embodiment, method 600 may includeestablishing a connection between charging component and electricaircraft and/or electric aircraft port. The electric aircraft port mayinclude nay electric aircraft port as described herein. The connectionmay include any connection as described herein. In a non-limitingembodiment, method 600 may include the sensor receiving the battery packdatum once the connection is successful.

With continued reference to FIG. 6 , method 600, at step 615, mayinclude generating a residual datum as a function of the at least anelectrical parameter and the battery pack datum. The residual datum mayinclude any residual datum as described herein. In a non-limitingembodiment, generating the residual datum may include prioritizing andcapturing any spikes of alternating current. Persons skilled in the art,upon reviewing the entirety of this disclosure, will be aware of thevarious methods of capturing and prioritizing specific data for purposesas described herein.

With continued reference to FIG. 6 , method 600, at step 620, mayinclude receiving, by a computing device, the residual datum. Thecomputing device may include any computing device as described herein.In a non-limiting embodiment, method 600 may include receiving any datumas a function of a network and/or network communication. The network mayinclude any network as described herein. The network communication mayinclude any network communication as described herein. In a non-limitingembodiment, method 600 may include receiving, by the computing device,any datum using physical CAN bus units. The physical CAN bus unit mayinclude any physical CAN bus unit as described herein.

With continued reference to FIG. 6 , method 600, at step 625, mayinclude identifying a residual element as a function of the residualdatum. The residual element may include any residual element asdescribed herein. In a non-limiting embodiment, method 600 may includecontinuously monitoring the source of the residual element.

With continued reference to FIG. 6 , method 600, at step 630, mayinclude generating an alert datum as a function of the residual element.The alert datum may include any alert datum as described herein. In anon-limiting embodiment, method 600 may include comparing the residualelement with a residual prediction datum. The residual prediction datummay be generated by computing device. The residual prediction datum mayinclude any residual prediction datum as described herein. In anon-limiting embodiment, method 600 may include determining that theresidual element is indeed a residual current, at least in part, togenerate alert datum 124, as a function of a residual threshold. Theresidual threshold may include any residual threshold as describedherein. Method 600, at step 630, may include using a timer module. Thetimer module may include any timer module as described herein.

With continued reference to FIG. 6 , method 600, at step 635, mayinclude executing a security measure as a function of the alert datum.The security measure may include any security measure as describedherein. In a non-limiting embodiment, method 600 may include generatingthe security measure using at least a machine-learning model and aresidual training set. The machine-learning model may include anymachine-learning model as described herein. The residual training setmay include any residual training set as described herein. In anon-limiting embodiment, method 600, at step 635, may include generatinga security measure as a function of operating a first mode. The firstmode may include any first mode as described herein. Method 600, at step635, may further include generating a security measure as a function ofoperating a second mode. The second mode may include any second mode asdescribed herein. Persons skilled in the art, upon reviewing theentirety of this disclosure, will be aware of the various methods ofusing one or more modes within the computing device for purposes asdescribed herein.

Referring now to FIG. 7 , an exemplary embodiment of an aircraft 700,which may include, or be incorporated with, a system for optimization ofa recharging flight plan is illustrated. As used in this disclosure an“aircraft” is any vehicle that may fly by gaining support from the air.As a non-limiting example, aircraft may include airplanes, helicopters,commercial and/or recreational aircrafts, instrument flight aircrafts,drones, electric aircrafts, airliners, rotorcrafts, vertical takeoff andlanding aircrafts, jets, airships, blimps, gliders, paramotors, and thelike thereof.

Still referring to FIG. 7 , aircraft 700 may include an electricallypowered aircraft. In embodiments, electrically powered aircraft may bean electric vertical takeoff and landing (eVTOL) aircraft. Aircraft 700may include an unmanned aerial vehicle and/or a drone. Electric aircraftmay be capable of rotor-based cruising flight, rotor-based takeoff,rotor-based landing, fixed-wing cruising flight, airplane-style takeoff,airplane-style landing, and/or any combination thereof. Electricaircraft may include one or more manned and/or unmanned aircrafts.Electric aircraft may include one or more all-electric short takeoff andlanding (eSTOL) aircrafts. For example, and without limitation, eSTOLaircrafts may accelerate the plane to a flight speed on takeoff anddecelerate the plane after landing. In an embodiment, and withoutlimitation, electric aircraft may be configured with an electricpropulsion assembly. Electric propulsion assembly may include anyelectric propulsion assembly as described in U.S. Nonprovisionalapplication Ser. No. 16/703,225, and entitled “AN INTEGRATED ELECTRICPROPULSION ASSEMBLY,” the entirety of which is incorporated herein byreference. For purposes of description herein, the terms “upper”,“lower”, “left”, “rear”, “right”, “front”, “vertical”, “horizontal”,“upward”, “downward”, “forward”, “backward” and derivatives thereofshall relate to the invention as oriented in FIG. 7 .

Still referring to FIG. 7 , aircraft 700 includes a fuselage 708. Asused in this disclosure a “fuselage” is the main body of an aircraft, orin other words, the entirety of the aircraft except for the cockpit,nose, wings, empennage, nacelles, any and all control surfaces, andgenerally contains an aircraft's payload. Fuselage 708 may includestructural elements that physically support a shape and structure of anaircraft. Structural elements may take a plurality of forms, alone or incombination with other types. Structural elements may vary depending ona construction type of aircraft such as without limitation a fuselage708. Fuselage 708 may comprise a truss structure. A truss structure maybe used with a lightweight aircraft and comprises welded steel tubetrusses. A “truss,” as used in this disclosure, is an assembly of beamsthat create a rigid structure, often in combinations of triangles tocreate three-dimensional shapes. A truss structure may alternativelycomprise wood construction in place of steel tubes, or a combinationthereof. In embodiments, structural elements may comprise steel tubesand/or wood beams. In an embodiment, and without limitation, structuralelements may include an aircraft skin. Aircraft skin may be layered overthe body shape constructed by trusses. Aircraft skin may comprise aplurality of materials such as plywood sheets, aluminum, fiberglass,and/or carbon fiber, the latter of which will be addressed in greaterdetail later herein.

In embodiments, and with continued reference to FIG. 7 , aircraftfuselage 708 may include and/or be constructed using geodesicconstruction. Geodesic structural elements may include stringers woundabout formers (which may be alternatively called station frames) inopposing spiral directions. A “stringer,” as used in this disclosure, isa general structural element that includes a long, thin, and rigid stripof metal or wood that is mechanically coupled to and spans a distancefrom, station frame to station frame to create an internal skeleton onwhich to mechanically couple aircraft skin. A former (or station frame)may include a rigid structural element that is disposed along a lengthof an interior of aircraft fuselage 708 orthogonal to a longitudinal(nose to tail) axis of the aircraft and may form a general shape offuselage 708. A former may include differing cross-sectional shapes atdiffering locations along fuselage 708, as the former is the structuralelement that informs the overall shape of a fuselage 708 curvature. Inembodiments, aircraft skin may be anchored to formers and strings suchthat the outer mold line of a volume encapsulated by formers andstringers comprises the same shape as aircraft 700 when installed. Inother words, former(s) may form a fuselage's ribs, and the stringers mayform the interstitials between such ribs. The spiral orientation ofstringers about formers may provide uniform robustness at any point onan aircraft fuselage such that if a portion sustains damage, anotherportion may remain largely unaffected. Aircraft skin may be mechanicallycoupled to underlying stringers and formers and may interact with afluid, such as air, to generate lift and perform maneuvers.

In an embodiment, and still referring to FIG. 7 , fuselage 708 mayinclude and/or be constructed using monocoque construction. Monocoqueconstruction may include a primary structure that forms a shell (or skinin an aircraft's case) and supports physical loads. Monocoque fuselagesare fuselages in which the aircraft skin or shell is also the primarystructure. In monocoque construction aircraft skin would support tensileand compressive loads within itself and true monocoque aircraft can befurther characterized by the absence of internal structural elements.Aircraft skin in this construction method is rigid and can sustain itsshape with no structural assistance form underlying skeleton-likeelements. Monocoque fuselage may comprise aircraft skin made fromplywood layered in varying grain directions, epoxy-impregnatedfiberglass, carbon fiber, or any combination thereof.

According to embodiments, and further referring to FIG. 7 , fuselage 708may include a semi-monocoque construction. Semi-monocoque construction,as used herein, is a partial monocoque construction, wherein a monocoqueconstruction is describe above detail. In semi-monocoque construction,aircraft fuselage 708 may derive some structural support from stressedaircraft skin and some structural support from underlying framestructure made of structural elements. Formers or station frames can beseen running transverse to the long axis of fuselage 708 with circularcutouts which are generally used in real-world manufacturing for weightsavings and for the routing of electrical harnesses and other modernon-board systems. In a semi-monocoque construction, stringers are thin,long strips of material that run parallel to fuselage's long axis.Stringers may be mechanically coupled to formers permanently, such aswith rivets. Aircraft skin may be mechanically coupled to stringers andformers permanently, such as by rivets as well. A person of ordinaryskill in the art will appreciate, upon reviewing the entirety of thisdisclosure, that there are numerous methods for mechanical fastening ofthe aforementioned components like screws, nails, dowels, pins, anchors,adhesives like glue or epoxy, or bolts and nuts, to name a few. A subsetof fuselage under the umbrella of semi-monocoque construction includesunibody vehicles. Unibody, which is short for “unitized body” oralternatively “unitary construction”, vehicles are characterized by aconstruction in which the body, floor plan, and chassis form a singlestructure. In the aircraft world, unibody may be characterized byinternal structural elements like formers and stringers beingconstructed in one piece, integral to the aircraft skin as well as anyfloor construction like a deck.

Still referring to FIG. 7 , stringers and formers, which may account forthe bulk of an aircraft structure excluding monocoque construction, maybe arranged in a plurality of orientations depending on aircraftoperation and materials. Stringers may be arranged to carry axial(tensile or compressive), shear, bending or torsion forces throughouttheir overall structure. Due to their coupling to aircraft skin,aerodynamic forces exerted on aircraft skin will be transferred tostringers. A location of said stringers greatly informs the type offorces and loads applied to each and every stringer, all of which may behandled by material selection, cross-sectional area, and mechanicalcoupling methods of each member. A similar assessment may be made forformers. In general, formers may be significantly larger incross-sectional area and thickness, depending on location, thanstringers. Both stringers and formers may comprise aluminum, aluminumalloys, graphite epoxy composite, steel alloys, titanium, or anundisclosed material alone or in combination.

In an embodiment, and still referring to FIG. 7 , stressed skin, whenused in semi-monocoque construction is the concept where the skin of anaircraft bears partial, yet significant, load in an overall structuralhierarchy. In other words, an internal structure, whether it be a frameof welded tubes, formers and stringers, or some combination, may not besufficiently strong enough by design to bear all loads. The concept ofstressed skin may be applied in monocoque and semi-monocoqueconstruction methods of fuselage 708. Monocoque comprises onlystructural skin, and in that sense, aircraft skin undergoes stress byapplied aerodynamic fluids imparted by the fluid. Stress as used incontinuum mechanics may be described in pound-force per square inch(lbf/in²) or Pascals (Pa). In semi-monocoque construction stressed skinmay bear part of aerodynamic loads and additionally may impart force onan underlying structure of stringers and formers.

Still referring to FIG. 7 , it should be noted that an illustrativeembodiment is presented only, and this disclosure in no way limits theform or construction method of a system and method for loading payloadinto an eVTOL aircraft. In embodiments, fuselage 708 may be configurablebased on the needs of the eVTOL per specific mission or objective. Thegeneral arrangement of components, structural elements, and hardwareassociated with storing and/or moving a payload may be added or removedfrom fuselage 708 as needed, whether it is stowed manually, automatedly,or removed by personnel altogether. Fuselage 708 may be configurable fora plurality of storage options. Bulkheads and dividers may be installedand uninstalled as needed, as well as longitudinal dividers wherenecessary. Bulkheads and dividers may be installed using integratedslots and hooks, tabs, boss and channel, or hardware like bolts, nuts,screws, nails, clips, pins, and/or dowels, to name a few. Fuselage 708may also be configurable to accept certain specific cargo containers, ora receptable that can, in turn, accept certain cargo containers.

Still referring to FIG. 7 , aircraft 700 may include a plurality oflaterally extending elements attached to fuselage 708. As used in thisdisclosure a “laterally extending element” is an element that projectsessentially horizontally from fuselage, including an outrigger, a spar,and/or a fixed wing that extends from fuselage. Wings may be structureswhich include airfoils configured to create a pressure differentialresulting in lift. Wings may generally dispose on the left and rightsides of the aircraft symmetrically, at a point between nose andempennage. Wings may comprise a plurality of geometries in planformview, swept swing, tapered, variable wing, triangular, oblong,elliptical, square, among others. A wing's cross section geometry maycomprise an airfoil. An “airfoil” as used in this disclosure is a shapespecifically designed such that a fluid flowing above and below it exertdiffering levels of pressure against the top and bottom surface. Inembodiments, the bottom surface of an aircraft can be configured togenerate a greater pressure than does the top, resulting in lift.Laterally extending element may comprise differing and/or similarcross-sectional geometries over its cord length or the length from wingtip to where wing meets the aircraft's body. One or more wings may besymmetrical about the aircraft's longitudinal plane, which comprises thelongitudinal or roll axis reaching down the center of the aircraftthrough the nose and empennage, and the plane's yaw axis. Laterallyextending element may comprise controls surfaces configured to becommanded by a pilot or pilots to change a wing's geometry and thereforeits interaction with a fluid medium, like air. Control surfaces maycomprise flaps, ailerons, tabs, spoilers, and slats, among others. Thecontrol surfaces may dispose on the wings in a plurality of locationsand arrangements and in embodiments may be disposed at the leading andtrailing edges of the wings, and may be configured to deflect up, down,forward, aft, or a combination thereof. An aircraft, including adual-mode aircraft may comprise a combination of control surfaces toperform maneuvers while flying or on ground.

Still referring to FIG. 7 , aircraft 700 includes a plurality of flightcomponents 704. As used in this disclosure a “flight component” is acomponent that promotes flight and guidance of an aircraft. In anembodiment, flight component 704 may be mechanically coupled to anaircraft. As used herein, a person of ordinary skill in the art wouldunderstand “mechanically coupled” to mean that at least a portion of adevice, component, or circuit is connected to at least a portion of theaircraft via a mechanical coupling. Said mechanical coupling caninclude, for example, rigid coupling, such as beam coupling, bellowscoupling, bushed pin coupling, constant velocity, split-muff coupling,diaphragm coupling, disc coupling, donut coupling, elastic coupling,flexible coupling, fluid coupling, gear coupling, grid coupling, hirthjoints, hydrodynamic coupling, jaw coupling, magnetic coupling, Oldhamcoupling, sleeve coupling, tapered shaft lock, twin spring coupling, ragjoint coupling, universal joints, or any combination thereof. In anembodiment, mechanical coupling may be used to connect the ends ofadjacent parts and/or objects of an electric aircraft. Further, in anembodiment, mechanical coupling may be used to join two pieces ofrotating electric aircraft components.

Still referring to FIG. 7 , plurality of flight components 704 mayinclude at least a lift propulsor component 712. As used in thisdisclosure a “lift propulsor component” is a component and/or deviceused to propel a craft upward by exerting downward force on a fluidmedium, which may include a gaseous medium such as air or a liquidmedium such as water. Lift propulsor component 712 may include anydevice or component that consumes electrical power on demand to propelan electric aircraft in a direction or other vehicle while on ground orin-flight. For example, and without limitation, lift propulsor component712 may include a rotor, propeller, paddle wheel and the like thereof,wherein a rotor is a component that produces torque along thelongitudinal axis, and a propeller produces torquer along the verticalaxis. In an embodiment, lift propulsor component 712 includes aplurality of blades. As used in this disclosure a “blade” is a propellerthat converts rotary motion from an engine or other power source into aswirling slipstream. In an embodiment, blade may convert rotary motionto push the propeller forwards or backwards. In an embodiment liftpropulsor component 712 may include a rotating power-driven hub, towhich are attached several radial airfoil-section blades such that thewhole assembly rotates about a longitudinal axis. Blades may beconfigured at an angle of attack, wherein an angle of attack isdescribed in detail below. In an embodiment, and without limitation,angle of attack may include a fixed angle of attack. As used in thisdisclosure a “fixed angle of attack” is fixed angle between a chord lineof a blade and relative wind. As used in this disclosure a “fixed angle”is an angle that is secured and/or unmovable from the attachment point.For example, and without limitation fixed angle of attack may be 3.2° asa function of a pitch angle of 19.7° and a relative wind angle 16.5°. Inanother embodiment, and without limitation, angle of attack may includea variable angle of attack. As used in this disclosure a “variable angleof attack” is a variable and/or moveable angle between a chord line of ablade and relative wind. As used in this disclosure a “variable angle”is an angle that is moveable from an attachment point. For example, andwithout limitation variable angle of attack may be a first angle of10.7° as a function of a pitch angle of 17.1° and a relative wind angle16.4°, wherein the angle adjusts and/or shifts to a second angle of16.7° as a function of a pitch angle of 16.1° and a relative wind angle16.4°. In an embodiment, angle of attack be configured to produce afixed pitch angle. As used in this disclosure a “fixed pitch angle” is afixed angle between a cord line of a blade and the rotational velocitydirection. For example, and without limitation, fixed pitch angle mayinclude 18°. In another embodiment fixed angle of attack may be manuallyvariable to a few set positions to adjust one or more lifts of theaircraft prior to flight. In an embodiment, blades for an aircraft aredesigned to be fixed to their hub at an angle similar to the thread on ascrew makes an angle to the shaft; this angle may be referred to as apitch or pitch angle which will determine a speed of forward movement asthe blade rotates.

In an embodiment, and still referring to FIG. 7 , lift propulsorcomponent 712 may be configured to produce a lift. As used in thisdisclosure a “lift” is a perpendicular force to the oncoming flowdirection of fluid surrounding the surface. For example, and withoutlimitation relative air speed may be horizontal to aircraft 700, whereinlift force may be a force exerted in a vertical direction, directingaircraft 700 upwards. In an embodiment, and without limitation, liftpropulsor component 712 may produce lift as a function of applying atorque to lift propulsor component. As used in this disclosure a“torque” is a measure of force that causes an object to rotate about anaxis in a direction. For example, and without limitation, torque mayrotate an aileron and/or rudder to generate a force that may adjustand/or affect altitude, airspeed velocity, groundspeed velocity,direction during flight, and/or thrust. For example, one or more flightcomponents such as a power sources may apply a torque on lift propulsorcomponent 712 to produce lift. As used in this disclosure a “powersource” is a source that that drives and/or controls any other flightcomponent. For example, and without limitation power source may includea motor that operates to move one or more lift propulsor components, todrive one or more blades, or the like thereof. A motor may be driven bydirect current (DC) electric power and may include, without limitation,brushless DC electric motors, switched reluctance motors, inductionmotors, or any combination thereof. A motor may also include electronicspeed controllers or other components for regulating motor speed,rotation direction, and/or dynamic braking.

Still referring to FIG. 7 , power source may include an energy source.An energy source may include, for example, an electrical energy source agenerator, a photovoltaic device, a fuel cell such as a hydrogen fuelcell, direct methanol fuel cell, and/or solid oxide fuel cell, anelectric energy storage device (e.g., a capacitor, an inductor, and/or abattery). An electrical energy source may also include a battery cell,or a plurality of battery cells connected in series into a module andeach module connected in series or in parallel with other modules.Configuration of an energy source containing connected modules may bedesigned to meet an energy or power requirement and may be designed tofit within a designated footprint in an electric aircraft in whichaircraft 700 may be incorporated.

In an embodiment, and still referring to FIG. 7 , an energy source maybe used to provide a steady supply of electrical power to a load overthe course of a flight by a vehicle or other electric aircraft. Forexample, an energy source may be capable of providing sufficient powerfor “cruising” and other relatively low-energy phases of flight. Anenergy source may also be capable of providing electrical power for somehigher-power phases of flight as well, particularly when the energysource is at a high SOC, as may be the case for instance during takeoff.In an embodiment, an energy source may be capable of providingsufficient electrical power for auxiliary loads including withoutlimitation, lighting, navigation, communications, de-icing, steering orother systems requiring power or energy. Further, an energy source maybe capable of providing sufficient power for controlled descent andlanding protocols, including, without limitation, hovering descent orrunway landing. As used herein an energy source may have high powerdensity where electrical power an energy source can usefully produce perunit of volume and/or mass is relatively high. “Electrical power,” asused in this disclosure, is defined as a rate of electrical energy perunit time. An energy source may include a device for which power thatmay be produced per unit of volume and/or mass has been optimized, atthe expense of the maximal total specific energy density or powercapacity, during design. Non-limiting examples of items that may be usedas at least an energy source may include batteries used for startingapplications including Li ion batteries which may include NCA, NMC,Lithium iron phosphate (LiFePO4) and Lithium Manganese Oxide (LMO)batteries, which may be mixed with another cathode chemistry to providemore specific power if the application requires Li metal batteries,which have a lithium metal anode that provides high power on demand, Liion batteries that have a silicon or titanite anode, energy source maybe used, in an embodiment, to provide electrical power to an electricaircraft or drone, such as an electric aircraft vehicle, during momentsrequiring high rates of power output, including without limitationtakeoff, landing, thermal de-icing and situations requiring greaterpower output for reasons of stability, such as high turbulencesituations, as described in further detail below. A battery may include,without limitation a battery using nickel based chemistries such asnickel cadmium or nickel metal hydride, a battery using lithium ionbattery chemistries such as a nickel cobalt aluminum (NCA), nickelmanganese cobalt (NMC), lithium iron phosphate (LiFePO4), lithium cobaltoxide (LCO), and/or lithium manganese oxide (LMO), a battery usinglithium polymer technology, lead-based batteries such as withoutlimitation lead acid batteries, metal-air batteries, or any othersuitable battery. Persons skilled in the art, upon reviewing theentirety of this disclosure, will be aware of various devices ofcomponents that may be used as an energy source.

Still referring to FIG. 7 , an energy source may include a plurality ofenergy sources, referred to herein as a module of energy sources. Amodule may include batteries connected in parallel or in series or aplurality of modules connected either in series or in parallel designedto deliver both the power and energy requirements of the application.Connecting batteries in series may increase the voltage of at least anenergy source which may provide more power on demand. High voltagebatteries may require cell matching when high peak load is needed. Asmore cells are connected in strings, there may exist the possibility ofone cell failing which may increase resistance in the module and reducean overall power output as a voltage of the module may decrease as aresult of that failing cell. Connecting batteries in parallel mayincrease total current capacity by decreasing total resistance, and italso may increase overall amp-hour capacity. Overall energy and poweroutputs of at least an energy source may be based on individual batterycell performance or an extrapolation based on measurement of at least anelectrical parameter. In an embodiment where an energy source includes aplurality of battery cells, overall power output capacity may bedependent on electrical parameters of each individual cell. If one cellexperiences high self-discharge during demand, power drawn from at leastan energy source may be decreased to avoid damage to the weakest cell.An energy source may further include, without limitation, wiring,conduit, housing, cooling system and battery management system. Personsskilled in the art will be aware, after reviewing the entirety of thisdisclosure, of many different components of an energy source.

In an embodiment and still referring to FIG. 7 , plurality of flightcomponents 704 may be arranged in a quad copter orientation. As used inthis disclosure a “quad copter orientation” is at least a lift propulsorcomponent oriented in a geometric shape and/or pattern, wherein each ofthe lift propulsor components are located along a vertex of thegeometric shape. For example, and without limitation, a square quadcopter orientation may have four lift propulsor components oriented inthe geometric shape of a square, wherein each of the four lift propulsorcomponents are located along the four vertices of the square shape. As afurther non-limiting example, a hexagonal quad copter orientation mayhave six lift propulsor components oriented in the geometric shape of ahexagon, wherein each of the six lift propulsor components are locatedalong the six vertices of the hexagon shape. In an embodiment, andwithout limitation, quad copter orientation may include a first set oflift propulsor components and a second set of lift propulsor components,wherein the first set of lift propulsor components and the second set oflift propulsor components may include two lift propulsor componentseach, wherein the first set of lift propulsor components and a secondset of lift propulsor components are distinct from one another. Forexample, and without limitation, the first set of lift propulsorcomponents may include two lift propulsor components that rotate in aclockwise direction, wherein the second set of lift propulsor componentsmay include two lift propulsor components that rotate in acounterclockwise direction. In an embodiment, and without limitation,the first set of propulsor lift components may be oriented along a lineoriented 30° from the longitudinal axis of aircraft 700. In anotherembodiment, and without limitation, the second set of propulsor liftcomponents may be oriented along a line oriented 135° from thelongitudinal axis, wherein the first set of lift propulsor componentsline and the second set of lift propulsor components are perpendicularto each other.

Still referring to FIG. 7 , plurality of flight components 704 mayinclude a pusher component 716. As used in this disclosure a “pushercomponent” is a component that pushes and/or thrusts an aircraft througha medium. As a non-limiting example, pusher component 716 may include apusher propeller, a paddle wheel, a pusher motor, a pusher propulsor,and the like. Additionally, or alternatively, pusher flight componentmay include a plurality of pusher flight components. Pusher component716 is configured to produce a forward thrust. As used in thisdisclosure a “forward thrust” is a thrust that forces aircraft through amedium in a horizontal direction, wherein a horizontal direction is adirection parallel to the longitudinal axis. As a non-limiting example,forward thrust may include a force of 1145 N to force aircraft to in ahorizontal direction along the longitudinal axis. As a furthernon-limiting example, forward thrust may include a force of, as anon-limiting example, 300 N to force aircraft 700 in a horizontaldirection along a longitudinal axis. As a further non-limiting example,pusher component 716 may twist and/or rotate to pull air behind it and,at the same time, push aircraft 700 forward with an equal amount offorce. In an embodiment, and without limitation, the more air forcedbehind aircraft, the greater the thrust force with which the aircraft ispushed horizontally will be. In another embodiment, and withoutlimitation, forward thrust may force aircraft 700 through the medium ofrelative air. Additionally or alternatively, plurality of flightcomponents 704 may include one or more puller components. As used inthis disclosure a “puller component” is a component that pulls and/ortows an aircraft through a medium. As a non-limiting example, pullercomponent may include a flight component such as a puller propeller, apuller motor, a tractor propeller, a puller propulsor, and the like.Additionally, or alternatively, puller component may include a pluralityof puller flight components.

In an embodiment and still referring to FIG. 7 , aircraft 700 mayinclude a flight controller located within fuselage 708, wherein aflight controller is described in detail below, in reference to FIG. 7 .In an embodiment, and without limitation, flight controller may beconfigured to operate a fixed-wing flight capability. As used in thisdisclosure a “fixed-wing flight capability” is a method of flightwherein the plurality of laterally extending elements generate lift. Forexample, and without limitation, fixed-wing flight capability maygenerate lift as a function of an airspeed of aircraft 70 and one ormore airfoil shapes of the laterally extending elements, wherein anairfoil is described above in detail. As a further non-limiting example,flight controller may operate the fixed-wing flight capability as afunction of reducing applied torque on lift propulsor component 712. Forexample, and without limitation, flight controller may reduce a torqueof 19 Nm applied to a first set of lift propulsor components to a torqueof 16 Nm. As a further non-limiting example, flight controller mayreduce a torque of 12 Nm applied to a first set of lift propulsorcomponents to a torque of 0 Nm. In an embodiment, and withoutlimitation, flight controller may produce fixed-wing flight capabilityas a function of increasing forward thrust exerted by pusher component716. For example, and without limitation, flight controller may increasea forward thrust of 1000 kN produced by pusher component 716 to aforward thrust of 1100 kN. In an embodiment, and without limitation, anamount of lift generation may be related to an amount of forward thrustgenerated to increase airspeed velocity, wherein the amount of liftgeneration may be directly proportional to the amount of forward thrustproduced. Additionally or alternatively, flight controller may includean inertia compensator. As used in this disclosure an “inertiacompensator” is one or more computing devices, electrical components,logic circuits, processors, and the like there of that are configured tocompensate for inertia in one or more lift propulsor components presentin aircraft 700. Inertia compensator may alternatively or additionallyinclude any computing device used as an inertia compensator as describedin U.S. Nonprovisional application Ser. No. 17/106,557, and entitled“SYSTEM AND METHOD FOR FLIGHT CONTROL IN ELECTRIC AIRCRAFT,” theentirety of which is incorporated herein by reference.

In an embodiment, and still referring to FIG. 7 , flight controller maybe configured to perform a reverse thrust command. As used in thisdisclosure a “reverse thrust command” is a command to perform a thrustthat forces a medium towards the relative air opposing the aircraft. Forexample, reverse thrust command may include a thrust of 180 N directedtowards the nose of aircraft to at least repel and/or oppose therelative air. Reverse thrust command may alternatively or additionallyinclude any reverse thrust command as described in U.S. Nonprovisionalapplication Ser. No. 17/319,155 and entitled “AIRCRAFT HAVING REVERSETHRUST CAPABILITIES,” the entirety of which is incorporated herein byreference. In another embodiment, flight controller may be configured toperform a regenerative drag operation. As used in this disclosure a“regenerative drag operation” is an operating condition of an aircraft,wherein the aircraft has a negative thrust and/or is reducing inairspeed velocity. For example, and without limitation, regenerativedrag operation may include a positive propeller speed and a negativepropeller thrust. Regenerative drag operation may alternatively oradditionally include any regenerative drag operation as described inU.S. Nonprovisional application Ser. No. 17/319,155.

In an embodiment, and still referring to FIG. 7 , flight controller maybe configured to perform a corrective action as a function of a failureevent. As used in this disclosure a “corrective action” is an actionconducted by the plurality of flight components to correct and/or altera movement of an aircraft. For example, and without limitation, acorrective action may include an action to reduce a yaw torque generatedby a failure event. Additionally or alternatively, corrective action mayinclude any corrective action as described in U.S. Nonprovisionalapplication Ser. No. 17/222,539, and entitled “AIRCRAFT FORSELF-NEUTRALIZING FLIGHT,” the entirety of which is incorporated hereinby reference. As used in this disclosure a “failure event” is a failureof a lift propulsor component of the plurality of lift propulsorcomponents. For example, and without limitation, a failure event maydenote a rotation degradation of a rotor, a reduced torque of a rotor,and the like thereof.

Referring now to FIG. 8 , an embodiment of sensor suite 800 is presentedin accordance with one or more embodiments of the present disclosure.The herein disclosed system and method may comprise a plurality ofsensors in the form of individual sensors or a sensor suite working intandem or individually. A sensor suite may include a plurality ofindependent sensors, as described herein, where any number of thedescribed sensors may be used to detect any number of physical orelectrical quantities associated with an aircraft power system or anelectrical energy storage system. Independent sensors may includeseparate sensors measuring physical or electrical quantities that may bepowered by and/or in communication with circuits independently, whereeach may signal sensor output to a control circuit such as a usergraphical interface. In a non-limiting example, there may be fourindependent sensors communicatively connected to charging component 132measuring operating conditions of the communication such as temperature,electrical characteristic such as voltage, amperage, resistance, orimpedance, or any other parameters and/or quantities as described inthis disclosure. In an embodiment, use of a plurality of independentsensors may result in redundancy configured to employ more than onesensor that measures the same phenomenon, those sensors being of thesame type, a combination of, or another type of sensor not disclosed, sothat in the event one sensor fails, the ability of sensor 88 to detectphenomenon is maintained.

Sensor suite 800 includes a moisture sensor 804. “Moisture”, as used inthis disclosure, is the presence of water, this may include vaporizedwater in air, condensation on the surfaces of objects, or concentrationsof liquid water. Moisture may include humidity. “Humidity”, as used inthis disclosure, is the property of a gaseous medium (almost always air)to hold water in the form of vapor. An amount of water vapor containedwithin a parcel of air can vary significantly. Water vapor is generallyinvisible to the human eye and may be damaging to electrical components.There are three primary measurements of humidity, absolute, relative,specific humidity. “Absolute humidity,” for the purposes of thisdisclosure, describes the water content of air and is expressed ineither grams per cubic meters or grams per kilogram. “Relativehumidity”, for the purposes of this disclosure, is expressed as apercentage, indicating a present stat of absolute humidity relative to amaximum humidity given the same temperature. “Specific humidity”, forthe purposes of this disclosure, is the ratio of water vapor mass tototal moist air parcel mass, where parcel is a given portion of agaseous medium. Moisture sensor 804 may be psychrometer. Moisture sensor804 may be a hygrometer. Moisture sensor 804 may be configured to act asor include a humidistat. A “humidistat”, for the purposes of thisdisclosure, is a humidity-triggered switch, often used to controlanother electronic device. Moisture sensor 804 may use capacitance tomeasure relative humidity and include in itself, or as an externalcomponent, include a device to convert relative humidity measurements toabsolute humidity measurements. “Capacitance”, for the purposes of thisdisclosure, is the ability of a system to store an electric charge, inthis case the system is a parcel of air which may be near, adjacent to,or above a battery cell.

With continued reference to FIG. 8 , sensor suite 800 may includeelectrical sensors 808. Electrical sensors 808 may be configured tomeasure voltage of charging component 132, electrical current ofcharging component 132, and resistance of charging component 132.Electrical sensors 808 may include separate sensors to measure each ofthe previously disclosed electrical characteristics such as voltmeter,ammeter, and ohmmeter, respectively.

Alternatively or additionally, and with continued reference to FIG. 8 ,sensor suite 800 may include a sensor or plurality thereof that maydetect voltage and direct the charging of individual battery cells of apower source according to charge level; detection may be performed usingany suitable component, set of components, and/or mechanism for director indirect measurement and/or detection of voltage levels, includingwithout limitation comparators, analog to digital converters, any formof voltmeter, or the like. Sensor suite 800 and/or a control circuitincorporated therein and/or communicatively connected thereto may beconfigured to adjust charge to one or more battery cells as a functionof a charge level and/or a detected parameter. For instance, and withoutlimitation, sensor suite 800 may be configured to determine that acharge level of a battery cell of a power source is high based on adetected voltage level of that battery cell or portion of the powersource and/or battery pack. Sensor suite 800 may alternatively oradditionally detect a charge reduction event, defined for purposes ofthis disclosure as any temporary or permanent state of a battery cellrequiring reduction or cessation of charging; a charge reduction eventmay include a cell being fully charged and/or a cell undergoing aphysical and/or electrical process that makes continued charging at acurrent voltage and/or current level inadvisable due to a risk that thecell will be damaged, will overheat, or the like. Detection of a chargereduction event may include detection of a temperature, of the cellabove a threshold level, detection of a voltage and/or resistance levelabove or below a threshold, or the like. Sensor suite 800 may includedigital sensors, analog sensors, or a combination thereof. Sensor suite800 may include digital-to-analog converters (DAC), analog-to-digitalconverters (ADC, A/D, A-to-D), a combination thereof, and the like.

With continued reference to FIG. 8 , sensor suite 800 may includethermocouples, thermistors, thermometers, passive infrared sensors,resistance temperature sensors (RTD's), semiconductor based integratedcircuits (IC), a combination thereof or another undisclosed sensor type,alone or in combination. Temperature, for the purposes of thisdisclosure, and as would be appreciated by someone of ordinary skill inthe art, is a measure of the heat energy of a system. Temperature, asmeasured by any number or combinations of sensors present within sensorsuite 800, may be measured in Fahrenheit (° F.), Celsius (° C.), Kelvin(° K), or another scale alone or in combination. The temperaturemeasured by sensors may comprise electrical signals which aretransmitted to their appropriate destination wireless or through a wiredconnection.

With continued reference to FIG. 8 , sensor suite 800 may include asensor configured to detect gas that may be emitted during or after acell failure. “Cell failure”, for the purposes of this disclosure,refers to a malfunction of a battery cell of a power source, which maybe an electrochemical cell, that renders the cell inoperable for itsdesigned function, namely providing electrical energy to at least aportion of an electric aircraft. Byproducts of cell failure 812 mayinclude gaseous discharge including oxygen, hydrogen, carbon dioxide,methane, carbon monoxide, a combination thereof, or another undisclosedgas, alone or in combination. Further the sensor configured to detectvent gas from electrochemical cells may comprise a gas detector. For thepurposes of this disclosure, a “gas detector” is a device used to detecta gas is present in an area. Gas detectors, and more specifically, thegas sensor that may be used in sensor suite 800, may be configured todetect combustible, flammable, toxic, oxygen depleted, a combinationthereof, or another type of gas alone or in combination. The gas sensorthat may be present in sensor suite 800 may include a combustible gas,photoionization detectors, electrochemical gas sensors, ultrasonicsensors, metal-oxide-semiconductor (MOS) sensors, infrared imagingsensors, a combination thereof, or another undisclosed type of gassensor alone or in combination. Sensor suite 800 may include sensorsthat are configured to detect non-gaseous byproducts of cell failure 812including, in non-limiting examples, liquid chemical leaks includingaqueous alkaline solution, ionomer, molten phosphoric acid, liquidelectrolytes with redox shuttle and ionomer, and salt water, amongothers. Sensor suite 800 may include sensors that are configured todetect non-gaseous byproducts of cell failure 812 including, innon-limiting examples, electrical anomalies as detected by any of theprevious disclosed sensors or components.

With continued reference to FIG. 8 , sensors 808 may be disposed on asense board 816. In one or more embodiments, sense board 816 may includeopposing flat surfaces and may be configured to cover a portion of abattery module within a power source, such as a battery pack. Senseboard 816 may include, without limitation, a control circuit configuredto perform and/or direct any actions performed by sense board 816 and/orany other component and/or element described in this disclosure. Senseboard 816 may be consistent with the sense board disclosed in U.S.patent application Ser. No. 16/948,140 entitled, “SYSTEM AND METHOD FORHIGH ENERGY DENSITY BATTERY MODULE” and incorporated herein by referencein its entirety.

With continued reference to FIG. 8 , sensor suite 800 may be configuredto detect events where voltage nears an upper voltage threshold or lowervoltage threshold. The upper voltage threshold may be stored in a memoryof, for example, a computing device for comparison with an instantmeasurement taken by any combination of sensors present within sensorsuite 800. The upper voltage threshold may be calculated and calibratedbased on factors relating to battery cell health, maintenance history,location within battery pack, designed application, and type, amongothers. Sensor suite 800 may measure voltage at an instant, over aperiod of time, or periodically. Sensor suite 800 may be configured tooperate at any of these detection modes, switch between modes, orsimultaneous measure in more than one mode. Sensor 88 may detect throughsensor suite 800 events where voltage nears the lower voltage threshold.The lower voltage threshold may indicate power loss to or from anindividual battery cell or portion of the battery pack. Sensor 88 maydetect through sensor suite 800 events where voltage exceeds the upperand lower voltage threshold. Events where voltage exceeds the upper andlower voltage threshold may indicate battery cell failure or electricalanomalies that could lead to potentially dangerous situations foraircraft and personnel that may be present in or near its operation.Additional disclosure related to a battery management system may befound in U.S. patent application Ser. Nos. 17/111,002 and 17/108,798entitled “SYSTEMS AND METHODS FOR A BATTERY MANAGEMENT SYSTEM INTEGRATEDIN A BATTERY PACK CONFIGURED FOR USE IN ELECTRIC AIRCRAFT”, both ofwhich are incorporated in their entirety herein by reference.

Exemplary methods of signal processing may include analog, continuoustime, discrete, digital, nonlinear, and statistical. Analog signalprocessing may be performed on non-digitized or analog signals.Exemplary analog processes may include passive filters, active filters,additive mixers, integrators, delay lines, compandors, multipliers,voltage-controlled filters, voltage-controlled oscillators, andphase-locked loops. Continuous-time signal processing may be used, insome cases, to process signals which varying continuously within adomain, for instance time. Exemplary non-limiting continuous timeprocesses may include time domain processing, frequency domainprocessing (Fourier transform), and complex frequency domain processing.Discrete time signal processing may be used when a signal is samplednon-continuously or at discrete time intervals (i.e., quantized intime). Analog discrete-time signal processing may process a signal usingthe following exemplary circuits sample and hold circuits, analogtime-division multiplexers, analog delay lines and analog feedback shiftregisters. Digital signal processing may be used to process digitizeddiscrete-time sampled signals. Commonly, digital signal processing maybe performed by a computing device or other specialized digitalcircuits, such as without limitation an application specific integratedcircuit (ASIC), a field-programmable gate array (FPGA), or a specializeddigital signal processor (DSP). Digital signal processing may be used toperform any combination of typical arithmetical operations, includingfixed-point and floating-point, real-valued and complex-valued,multiplication and addition. Digital signal processing may additionallyoperate circular buffers and lookup tables. Further non-limitingexamples of algorithms that may be performed according to digital signalprocessing techniques include fast Fourier transform (FFT), finiteimpulse response (FIR) filter, infinite impulse response (IIR) filter,and adaptive filters such as the Wiener and Kalman filters. Statisticalsignal processing may be used to process a signal as a random function(i.e., a stochastic process), utilizing statistical properties. Forinstance, in some embodiments, a signal may be modeled with aprobability distribution indicating noise, which then may be used toreduce noise in a processed signal.

Referring now to FIG. 9 , an exemplary embodiment of a machine-learningmodule 900 that may perform one or more machine-learning processes asdescribed in this disclosure is illustrated. Machine-learning module mayperform determinations, classification, and/or analysis steps, methods,processes, or the like as described in this disclosure using machinelearning processes. A “machine learning process,” as used in thisdisclosure, is a process that automatedly uses training data 904 togenerate an algorithm that will be performed by a computingdevice/module to produce outputs 908 given data provided as inputs 912;this is in contrast to a non-machine learning software program where thecommands to be executed are determined in advance by a user and writtenin a programming language.

Still referring to FIG. 9 , “training data,” as used herein, is datacontaining correlations that a machine-learning process may use to modelrelationships between two or more categories of data elements. Forinstance, and without limitation, training data 904 may include aplurality of data entries, each entry representing a set of dataelements that were recorded, received, and/or generated together; dataelements may be correlated by shared existence in a given data entry, byproximity in a given data entry, or the like. Multiple data entries intraining data 904 may evince one or more trends in correlations betweencategories of data elements; for instance, and without limitation, ahigher value of a first data element belonging to a first category ofdata element may tend to correlate to a higher value of a second dataelement belonging to a second category of data element, indicating apossible proportional or other mathematical relationship linking valuesbelonging to the two categories. Multiple categories of data elementsmay be related in training data 904 according to various correlations;correlations may indicate causative and/or predictive links betweencategories of data elements, which may be modeled as relationships suchas mathematical relationships by machine-learning processes as describedin further detail below. Training data 904 may be formatted and/ororganized by categories of data elements, for instance by associatingdata elements with one or more descriptors corresponding to categoriesof data elements. As a non-limiting example, training data 904 mayinclude data entered in standardized forms by persons or processes, suchthat entry of a given data element in a given field in a form may bemapped to one or more descriptors of categories. Elements in trainingdata 904 may be linked to descriptors of categories by tags, tokens, orother data elements; for instance, and without limitation, training data904 may be provided in fixed-length formats, formats linking positionsof data to categories such as comma-separated value (CSV) formats and/orself-describing formats such as extensible markup language (XML),JavaScript Object Notation (JSON), or the like, enabling processes ordevices to detect categories of data.

Alternatively or additionally, and continuing to refer to FIG. 9 ,training data 904 may include one or more elements that are notcategorized; that is, training data 904 may not be formatted or containdescriptors for some elements of data. Machine-learning algorithmsand/or other processes may sort training data 904 according to one ormore categorizations using, for instance, natural language processingalgorithms, tokenization, detection of correlated values in raw data andthe like; categories may be generated using correlation and/or otherprocessing algorithms. As a non-limiting example, in a corpus of text,phrases making up a number “n” of compound words, such as nouns modifiedby other nouns, may be identified according to a statisticallysignificant prevalence of n-grams containing such words in a particularorder; such an n-gram may be categorized as an element of language suchas a “word” to be tracked similarly to single words, generating a newcategory as a result of statistical analysis. Similarly, in a data entryincluding some textual data, a person's name may be identified byreference to a list, dictionary, or other compendium of terms,permitting ad-hoc categorization by machine-learning algorithms, and/orautomated association of data in the data entry with descriptors or intoa given format. The ability to categorize data entries automatedly mayenable the same training data 904 to be made applicable for two or moredistinct machine-learning algorithms as described in further detailbelow. Training data 904 used by machine-learning module 900 maycorrelate any input data as described in this disclosure to any outputdata as described in this disclosure. As a non-limiting illustrativeexample the residual element may be an input for an output of the alertdatum. In another non-limiting example, the alert datum may be an inputfor the output of the security measure.

Further referring to FIG. 9 , training data may be filtered, sorted,and/or selected using one or more supervised and/or unsupervisedmachine-learning processes and/or models as described in further detailbelow; such models may include without limitation a training dataclassifier 916. Training data classifier 916 may include a “classifier,”which as used in this disclosure is a machine-learning model as definedbelow, such as a mathematical model, neural net, or program generated bya machine learning algorithm known as a “classification algorithm,” asdescribed in further detail below, that sorts inputs into categories orbins of data, outputting the categories or bins of data and/or labelsassociated therewith. A classifier may be configured to output at leasta datum that labels or otherwise identifies a set of data that areclustered together, found to be close under a distance metric asdescribed below, or the like. Machine-learning module 900 may generate aclassifier using a classification algorithm, defined as a processeswhereby a computing device and/or any module and/or component operatingthereon derives a classifier from training data 904. Classification maybe performed using, without limitation, linear classifiers such aswithout limitation logistic regression and/or naive Bayes classifiers,nearest neighbor classifiers such as k-nearest neighbors classifiers,support vector machines, least squares support vector machines, fisher'slinear discriminant, quadratic classifiers, decision trees, boostedtrees, random forest classifiers, learning vector quantization, and/orneural network-based classifiers. As a non-limiting example, trainingdata classifier 916 may classify elements of training data to variouslevels of trip class, levels of severity of the residual element, andthe like thereof, for which a subset of training data may be selected.

Still referring to FIG. 9 , machine-learning module 900 may beconfigured to perform a lazy-learning process 920 and/or protocol, whichmay alternatively be referred to as a “lazy loading” or“call-when-needed” process and/or protocol, may be a process wherebymachine learning is conducted upon receipt of an input to be convertedto an output, by combining the input and training set to derive thealgorithm to be used to produce the output on demand. For instance, aninitial set of simulations may be performed to cover an initialheuristic and/or “first guess” at an output and/or relationship. As anon-limiting example, an initial heuristic may include a ranking ofassociations between inputs and elements of training data 904. Heuristicmay include selecting some number of highest-ranking associations and/ortraining data 904 elements. Lazy learning may implement any suitablelazy learning algorithm, including without limitation a K-nearestneighbors algorithm, a lazy naïve Bayes algorithm, or the like; personsskilled in the art, upon reviewing the entirety of this disclosure, willbe aware of various lazy-learning algorithms that may be applied togenerate outputs as described in this disclosure, including withoutlimitation lazy learning applications of machine-learning algorithms asdescribed in further detail below.

Alternatively or additionally, and with continued reference to FIG. 9 ,machine-learning processes as described in this disclosure may be usedto generate machine-learning models 924. A “machine-learning model,” asused in this disclosure, is a mathematical and/or algorithmicrepresentation of a relationship between inputs and outputs, asgenerated using any machine-learning process including withoutlimitation any process as described above, and stored in memory; aninput is submitted to a machine-learning model 924 once created, whichgenerates an output based on the relationship that was derived. Forinstance, and without limitation, a linear regression model, generatedusing a linear regression algorithm, may compute a linear combination ofinput data using coefficients derived during machine-learning processesto calculate an output datum. As a further non-limiting example, amachine-learning model 924 may be generated by creating an artificialneural network, such as a convolutional neural network comprising aninput layer of nodes, one or more intermediate layers, and an outputlayer of nodes. Connections between nodes may be created via the processof “training” the network, in which elements from a training data 904set are applied to the input nodes, a suitable training algorithm (suchas Levenberg-Marquardt, conjugate gradient, simulated annealing, orother algorithms) is then used to adjust the connections and weightsbetween nodes in adjacent layers of the neural network to produce thedesired values at the output nodes. This process is sometimes referredto as deep learning.

Still referring to FIG. 9 , machine-learning algorithms may include atleast a supervised machine-learning process 928. At least a supervisedmachine-learning process 928, as defined herein, include algorithms thatreceive a training set relating a number of inputs to a number ofoutputs, and seek to find one or more mathematical relations relatinginputs to outputs, where each of the one or more mathematical relationsis optimal according to some criterion specified to the algorithm usingsome scoring function. For instance, a supervised learning algorithm mayinclude any inputs as described above as inputs, any outputs asdescribed about as outputs, and a scoring function representing adesired form of relationship to be detected between inputs and outputs;scoring function may, for instance, seek to maximize the probabilitythat a given input and/or combination of elements inputs is associatedwith a given output to minimize the probability that a given input isnot associated with a given output. Scoring function may be expressed asa risk function representing an “expected loss” of an algorithm relatinginputs to outputs, where loss is computed as an error functionrepresenting a degree to which a prediction generated by the relation isincorrect when compared to a given input-output pair provided intraining data 904. Persons skilled in the art, upon reviewing theentirety of this disclosure, will be aware of various possiblevariations of at least a supervised machine-learning process 928 thatmay be used to determine relation between inputs and outputs. Supervisedmachine-learning processes may include classification algorithms asdefined above.

Further referring to FIG. 9 , machine learning processes may include atleast an unsupervised machine-learning processes 932. An unsupervisedmachine-learning process, as used herein, is a process that derivesinferences in datasets without regard to labels; as a result, anunsupervised machine-learning process may be free to discover anystructure, relationship, and/or correlation provided in the data.Unsupervised processes may not require a response variable; unsupervisedprocesses may be used to find interesting patterns and/or inferencesbetween variables, to determine a degree of correlation between two ormore variables, or the like.

Still referring to FIG. 9 , machine-learning module 900 may be designedand configured to create a machine-learning model 924 using techniquesfor development of linear regression models. Linear regression modelsmay include ordinary least squares regression, which aims to minimizethe square of the difference between predicted outcomes and actualoutcomes according to an appropriate norm for measuring such adifference (e.g. a vector-space distance norm); coefficients of theresulting linear equation may be modified to improve minimization.Linear regression models may include ridge regression methods, where thefunction to be minimized includes the least-squares function plus termmultiplying the square of each coefficient by a scalar amount topenalize large coefficients. Linear regression models may include leastabsolute shrinkage and selection operator (LASSO) models, in which ridgeregression is combined with multiplying the least-squares term by afactor of 1 divided by double the number of samples. Linear regressionmodels may include a multi-task lasso model wherein the norm applied inthe least-squares term of the lasso model is the Frobenius normamounting to the square root of the sum of squares of all terms. Linearregression models may include the elastic net model, a multi-taskelastic net model, a least angle regression model, a LARS lasso model,an orthogonal matching pursuit model, a Bayesian regression model, alogistic regression model, a stochastic gradient descent model, aperceptron model, a passive aggressive algorithm, a robustnessregression model, a Huber regression model, or any other suitable modelthat may occur to persons skilled in the art upon reviewing the entiretyof this disclosure. Linear regression models may be generalized in anembodiment to polynomial regression models, whereby a polynomialequation (e.g. a quadratic, cubic or higher-order equation) providing abest predicted output/actual output fit is sought; similar methods tothose described above may be applied to minimize error functions, aswill be apparent to persons skilled in the art upon reviewing theentirety of this disclosure.

Continuing to refer to FIG. 9 , machine-learning algorithms may include,without limitation, linear discriminant analysis. Machine-learningalgorithm may include quadratic discriminate analysis. Machine-learningalgorithms may include kernel ridge regression. Machine-learningalgorithms may include support vector machines, including withoutlimitation support vector classification-based regression processes.Machine-learning algorithms may include stochastic gradient descentalgorithms, including classification and regression algorithms based onstochastic gradient descent. Machine-learning algorithms may includenearest neighbors algorithms. Machine-learning algorithms may includevarious forms of latent space regularization such as variationalregularization. Machine-learning algorithms may include Gaussianprocesses such as Gaussian Process Regression. Machine-learningalgorithms may include cross-decomposition algorithms, including partialleast squares and/or canonical correlation analysis. Machine-learningalgorithms may include naïve Bayes methods. Machine-learning algorithmsmay include algorithms based on decision trees, such as decision treeclassification or regression algorithms. Machine-learning algorithms mayinclude ensemble methods such as bagging meta-estimator, forest ofrandomized tress, AdaBoost, gradient tree boosting, and/or votingclassifier methods. Machine-learning algorithms may include neural netalgorithms, including convolutional neural net processes.

It is to be noted that any one or more of the aspects and embodimentsdescribed herein may be conveniently implemented using one or moremachines (e.g., one or more computing devices that are utilized as auser computing device for an electronic document, one or more serverdevices, such as a document server, etc.) programmed according to theteachings of the present specification, as will be apparent to those ofordinary skill in the computer art. Appropriate software coding canreadily be prepared by skilled programmers based on the teachings of thepresent disclosure, as will be apparent to those of ordinary skill inthe software art. Aspects and implementations discussed above employingsoftware and/or software modules may also include appropriate hardwarefor assisting in the implementation of the machine executableinstructions of the software and/or software module.

Such software may be a computer program product that employs amachine-readable storage medium. A machine-readable storage medium maybe any medium that is capable of storing and/or encoding a sequence ofinstructions for execution by a machine (e.g., a computing device) andthat causes the machine to perform any one of the methodologies and/orembodiments described herein. Examples of a machine-readable storagemedium include, but are not limited to, a magnetic disk, an optical disc(e.g., CD, CD-R, DVD, DVD-R, etc.), a magneto-optical disk, a read-onlymemory “ROM” device, a random access memory “RAM” device, a magneticcard, an optical card, a solid-state memory device, an EPROM, an EEPROM,and any combinations thereof. A machine-readable medium, as used herein,is intended to include a single medium as well as a collection ofphysically separate media, such as, for example, a collection of compactdiscs or one or more hard disk drives in combination with a computermemory. As used herein, a machine-readable storage medium does notinclude transitory forms of signal transmission.

Such software may also include information (e.g., data) carried as adata signal on a data carrier, such as a carrier wave. For example,machine-executable information may be included as a data-carrying signalembodied in a data carrier in which the signal encodes a sequence ofinstruction, or portion thereof, for execution by a machine (e.g., acomputing device) and any related information (e.g., data structures anddata) that causes the machine to perform any one of the methodologiesand/or embodiments described herein.

Examples of a computing device include, but are not limited to, anelectronic book reading device, a computer workstation, a terminalcomputer, a server computer, a handheld device (e.g., a tablet computer,a smartphone, etc.), a web appliance, a network router, a networkswitch, a network bridge, any machine capable of executing a sequence ofinstructions that specify an action to be taken by that machine, and anycombinations thereof. In one example, a computing device may includeand/or be included in a kiosk.

FIG. 10 shows a diagrammatic representation of one embodiment of acomputing device in the exemplary form of a computer system 1000 withinwhich a set of instructions for causing a control system to perform anyone or more of the aspects and/or methodologies of the presentdisclosure may be executed. It is also contemplated that multiplecomputing devices may be utilized to implement a specially configuredset of instructions for causing one or more of the devices to performany one or more of the aspects and/or methodologies of the presentdisclosure. Computer system 1000 includes a processor 1004 and a memory1008 that communicate with each other, and with other components, via abus 1012. Bus 1012 may include any of several types of bus structuresincluding, but not limited to, a memory bus, a memory controller, aperipheral bus, a local bus, and any combinations thereof, using any ofa variety of bus architectures.

Processor 1004 may include any suitable processor, such as withoutlimitation a processor incorporating logical circuitry for performingarithmetic and logical operations, such as an arithmetic and logic unit(ALU), which may be regulated with a state machine and directed byoperational inputs from memory and/or sensors; processor 1004 may beorganized according to Von Neumann and/or Harvard architecture as anon-limiting example. Processor 1004 may include, incorporate, and/or beincorporated in, without limitation, a microcontroller, microprocessor,digital signal processor (DSP), Field Programmable Gate Array (FPGA),Complex Programmable Logic Device (CPLD), Graphical Processing Unit(GPU), general purpose GPU, Tensor Processing Unit (TPU), analog ormixed signal processor, Trusted Platform Module (TPM), a floating pointunit (FPU), and/or system on a chip (SoC).

Memory 1008 may include various components (e.g., machine-readablemedia) including, but not limited to, a random-access memory component,a read only component, and any combinations thereof. In one example, abasic input/output system 1016 (BIOS), including basic routines thathelp to transfer information between elements within computer system1000, such as during start-up, may be stored in memory 1008. Memory 1008may also include (e.g., stored on one or more machine-readable media)instructions (e.g., software) 1020 embodying any one or more of theaspects and/or methodologies of the present disclosure. In anotherexample, memory 1008 may further include any number of program modulesincluding, but not limited to, an operating system, one or moreapplication programs, other program modules, program data, and anycombinations thereof.

Computer system 1000 may also include a storage device 1024. Examples ofa storage device (e.g., storage device 1024) include, but are notlimited to, a hard disk drive, a magnetic disk drive, an optical discdrive in combination with an optical medium, a solid-state memorydevice, and any combinations thereof. Storage device 1024 may beconnected to bus 1012 by an appropriate interface (not shown). Exampleinterfaces include, but are not limited to, SCSI, advanced technologyattachment (ATA), serial ATA, universal serial bus (USB), IEEE 1394(FIREWIRE), and any combinations thereof. In one example, storage device1024 (or one or more components thereof) may be removably interfacedwith computer system 1000 (e.g., via an external port connector (notshown)). Particularly, storage device 1024 and an associatedmachine-readable medium 1028 may provide nonvolatile and/or volatilestorage of machine-readable instructions, data structures, programmodules, and/or other data for computer system 1000. In one example,software 1020 may reside, completely or partially, withinmachine-readable medium 1028. In another example, software 1020 mayreside, completely or partially, within processor 1004.

Computer system 1000 may also include an input device 1032. In oneexample, a user of computer system 1000 may enter commands and/or otherinformation into computer system 1000 via input device 1032. Examples ofan input device 1032 include, but are not limited to, an alpha-numericinput device (e.g., a keyboard), a pointing device, a joystick, agamepad, an audio input device (e.g., a microphone, a voice responsesystem, etc.), a cursor control device (e.g., a mouse), a touchpad, anoptical scanner, a video capture device (e.g., a still camera, a videocamera), a touchscreen, and any combinations thereof. Input device 1032may be interfaced to bus 1012 via any of a variety of interfaces (notshown) including, but not limited to, a serial interface, a parallelinterface, a game port, a USB interface, a FIREWIRE interface, a directinterface to bus 1012, and any combinations thereof. Input device 1032may include a touch screen interface that may be a part of or separatefrom display 1036, discussed further below. Input device 1032 may beutilized as a user selection device for selecting one or more graphicalrepresentations in a graphical interface as described above.

A user may also input commands and/or other information to computersystem 1000 via storage device 1024 (e.g., a removable disk drive, aflash drive, etc.) and/or network interface device 1040. A networkinterface device, such as network interface device 1040, may be utilizedfor connecting computer system 1000 to one or more of a variety ofnetworks, such as network 1044, and one or more remote devices 1048connected thereto. Examples of a network interface device include, butare not limited to, a network interface card (e.g., a mobile networkinterface card, a LAN card), a modem, and any combination thereof.Examples of a network include, but are not limited to, a wide areanetwork (e.g., the Internet, an enterprise network), a local areanetwork (e.g., a network associated with an office, a building, a campusor other relatively small geographic space), a telephone network, a datanetwork associated with a telephone/voice provider (e.g., a mobilecommunications provider data and/or voice network), a direct connectionbetween two computing devices, and any combinations thereof. A network,such as network 1044, may employ a wired and/or a wireless mode ofcommunication. In general, any network topology may be used. Information(e.g., data, software 1020, etc.) may be communicated to and/or fromcomputer system 1000 via network interface device 1040.

Computer system 1000 may further include a video display adapter 1052for communicating a displayable image to a display device, such asdisplay device 1036. Examples of a display device include, but are notlimited to, a liquid crystal display (LCD), a cathode ray tube (CRT), aplasma display, a light emitting diode (LED) display, and anycombinations thereof. Display adapter 1052 and display device 1036 maybe utilized in combination with processor 1004 to provide graphicalrepresentations of aspects of the present disclosure. In addition to adisplay device, computer system 1000 may include one or more otherperipheral output devices including, but not limited to, an audiospeaker, a printer, and any combinations thereof. Such peripheral outputdevices may be connected to bus 1012 via a peripheral interface 1056.Examples of a peripheral interface include, but are not limited to, aserial port, a USB connection, a FIREWIRE connection, a parallelconnection, and any combinations thereof.

The foregoing has been a detailed description of illustrativeembodiments of the invention. Various modifications and additions can bemade without departing from the spirit and scope of this invention.Features of each of the various embodiments described above may becombined with features of other described embodiments as appropriate inorder to provide a multiplicity of feature combinations in associatednew embodiments. Furthermore, while the foregoing describes a number ofseparate embodiments, what has been described herein is merelyillustrative of the application of the principles of the presentinvention. Additionally, although particular methods herein may beillustrated and/or described as being performed in a specific order, theordering is highly variable within ordinary skill to achieve methods andsystems according to the present disclosure. Accordingly, thisdescription is meant to be taken only by way of example, and not tootherwise limit the scope of this invention.

Exemplary embodiments have been disclosed above and illustrated in theaccompanying drawings. It will be understood by those skilled in the artthat various changes, omissions and additions may be made to that whichis specifically disclosed herein without departing from the spirit andscope of the present invention.

What is claimed is:
 1. A system for managing residual energy for anelectric aircraft port, wherein the system comprises: an electricaircraft port of an electric aircraft, the electric aircraft portconfigured to facilitate communication between a charging component andthe electric aircraft via a charging connection; a battery packconnected to the electric aircraft port, wherein the battery packcomprises: a plurality of battery modules; and a pack monitor unitconfigured to generate a battery pack datum, wherein the pack monitorunit comprises at least a controller, wherein electrical energy istransferred between the battery pack and the charging component via thecharging connection; a sensor connected to the electric aircraft port,wherein the sensor is configured to: detect an electrical parameter ofthe charging component when the charging component is in communicationwith the electric aircraft; and generate a residual datum as a functionof the electrical parameter and the battery pack datum; and a computingdevice comprising at least a processor, wherein the computing device isconfigured to: receive the residual datum from the sensor; identify aresidual element as a function of the residual datum, wherein theresidual element comprises at least a leakage current; and execute asecurity measure as a function of the identification.
 2. The system ofclaim 1, wherein identifying the residual element further comprisesidentifying an unsecure connection between the electric aircraft portand the charging component.
 3. The system of claim 1, wherein executingthe security measure further comprises relaying information about theresidual element to a user.
 4. The system of claim 1, wherein executingthe security measure comprises terminating the charging connectionbetween the electric aircraft port and the charging component.
 5. Thesystem of claim 4, wherein terminating the charging connection includesdisconnecting the electric aircraft port from the charging component. 6.The system of claim 1, wherein the security measure comprises a safetylock instruction, wherein the safety lock instruction comprisesunlocking a fastener of the charging component to disconnect theelectric aircraft port and the charging component.
 7. The system ofclaim 1, wherein the computing device is further configured to determinethe residual element using a residual threshold.
 8. The system of claim1, wherein the security measure is selected based on a magnitude of theresidual element.
 9. The system of claim 1, wherein the security measureis executed as a function of a trip class.
 10. The system of claim 1,wherein the computing device is configured to execute the securitymeasure on the electric aircraft port.
 11. The system of claim 1,wherein the computing device is further configured to terminate aconnection of a battery component to neighboring battery components ofthe battery component.
 12. The system of claim 1, wherein the electricaircraft further comprises an electric vertical take-off and landingaircraft.
 13. A method for managing residual energy for an electricaircraft port, wherein the method comprises: generating, by at least apack monitor unit of a battery pack, a battery pack datum from a batterypack of an electric aircraft, wherein the pack monitor unit comprises atleast a controller; creating a charging connection between an electricaircraft port of the electric aircraft and a charging component;detecting, by a sensor connected to the electric aircraft port, anelectrical parameter of the charging component; generating, by thesensor, a residual datum as a function of the electrical parameter andthe battery pack datum; receiving, by a computing device comprising atleast a processor, the residual datum; identifying a residual element asa function of the residual datum, wherein the residual element comprisesat least a leakage current; and executing a security measure as afunction of the identification.
 14. The method of claim 13, whereinexecuting the security measure comprises relaying information about theresidual element to a user.
 15. The method of claim 13, whereinexecuting the security measure comprises terminating the chargingconnection between the electric aircraft port and the chargingcomponent.
 16. The method of claim 15, wherein terminating the chargingconnection includes disconnecting the electric aircraft port from thecharging component.
 17. The method of claim 13, wherein the computingdevice is further configured to determine the residual element using aresidual threshold.
 18. The method of claim 13, wherein the securitymeasure is selected based on a magnitude of the residual element. 19.The method of claim 13, wherein the computing device is configured toexecute the security measure on the electric aircraft port.
 20. Themethod of claim 13, wherein the method further comprises terminating aconnection of a battery component to neighboring battery components ofthe battery component.